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Full text of "LANDSAT-2 launch and flight activation. Launch through orbit 50 and orbit adjust operation"

PACE 
IIVISIOIM 













DOCUMENTATION BRANCH 
CODE 256 



Ay/)s/9cf9-yy3'7yy 



75SDS4215 
21 MARCH 1975 



{NASA-CE-n3 7it4) LANDSAT-2 LAUNCH AND 

FLIGHT ACTIVATION, LAUNCH THROUGH OSBIT 50 

AND ORBIT ADJUST OPERATION Evaluation 

Report, 22-26 Jan. 1975 (General Electric 

Co., Beltsville. Md,l 263 d HC $8.50 63/13 



;;\ 



N75-23630 



Unclas 
2U33 



LANDSAT 2 LAUNCH AND FLIGHT ACTIVATION 

EVALUATION REPORT 

22 TO 26 JANUARY 1975 

LAUNCH THROUGH ORBIT 50 

AND ORBIT ADJUST OPERATION 

Prepared by 
GE LANDSAT OPERATION CONTROL CENTER 

For 

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

Goddard Space Flight Center 

Greenbelt, Maryland 20771 




GENERAL® ELECTRIC 



C^dntract NAS5-21808 



75SDS4215 
21 MARCH 1975 

LANDSAT 2 LAUNCH AND FLIGHT ACTIVATION 

EVALUATION REPORT 

22 TO 26 JANUARY 1975 

LAUNCH THROUGH ORBIT 50 

AND ORBIT ADJUST OPERATION 

Prepared by 
GE LANDSAT OPERATION CONTROL CENTER 

For 

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 

Goddard Space Flight Center 

Greenbelt, Maryland 20771 

Contract NAS5-21808 



Approved: 



jMMiQ U). WyfdUoAz 



Thomas W. Winchester 




SPACE DIVISION 

Valley Forge Space Center 
P. 0. Box 8555 • Philadelphia, Penna. 19101 




GENERAL@ELECTRIC 




t'am^j&^s %*-r>*-^j!Stgtos^iwvji i^^s Y^. v^-'" jL- ■:yr'^^'ste<!fJsS:■VihR^r1.:l - " ;- ,-^ ' ' • +r ' . 



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^4 '^'^ 



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OmmAL PAGE IS 
OF POOR OUALITY 



m 



OBSERVATORY CONFIGURATION 



Solar Array Panels 



Orbit Adjust Subsystem Thruster 



Attitude Measurement System. 
S-Band Antenna 



Connand Antenna 




Data 

Collection 

Antenna 



Attitude Control Subsystem 



Return Beam 

Vidicon Cameras 

(3) 



WBVTR Electronics 



Quadraloop Antenna 
(NHF) 



Wide Band Antennas 
(2) 



ulti -Spectral 
Scanner 



s 




°^«»~^?^ 



IV 




ORIGINAL PAGE re 
Of POOR Qvfu^ 



V 




LANDS AT Observatory Launch Configuration 






■*•§& 



vl 



TABLE OF CONTENTS 

Section Page 

1 Introduction • 1-1 

2 Summary ♦ . 2-1 

3 Spacecraft Activation Sequence 3-1 

4 Orbital Parameters 4-1 

5 Power Subsystem • 5-1 

6 Attitude Control Subsystem . . . • • 6-1 

7 Telemetry Subsystem * • 7-1 

8 Command/Clock Subsystem 8-1 

9 Orbit Adjust Subsystem (OAS) 9-1 

10 Magnetic Moment Compensating Assembly (MMCA), ..••». 10-1 

11 Unified S-Band/Premodulation Processor 11-1 

12 Separation and Unfold Subsystem 12-1 

13 Electrical Interface Subsystem 13-1 

14 Thermal Control Subsystem 14-1 

15 Narrowband Tape Recorder (NBTR) 15-1 

16 Wide Band Telemetry Subsystem 16-1 

17 Attitude Measurement Sensor (AMS) 17-1 

18 Wide Band Video Tape Recorders (WBVTR) 18-1 

19 Return Beam Vidicon Subsystem (RBV) 19-1 

20 Multispectral Scanner Subsystem 20-1 

21 Data Collection Subsystem 21-1 

Appendix A: LANDSAT-2 Configuration A-1 

Appendix B: Command Matrix B-1 

Appendix C: Telemetry Matrix • . . C-1 

Appendix D: Strip Chart Pay load Signatures D-1 

Appendix E: MSS Photographs , E-1 

Appendix F: DCS Operations in LANDSAT-2 (PIR-1N23-ERTS-130) ... F-1 

Appendix G; Spacecraft Orbit Reference Table . * G-1 



Vll 



LEST OF ILLUSTRATIONS 

Figure Page 

4-1 Subsatellite Plot of the LANDSAT-2 Spacecraft 4-3 

5-1 Functional Block Diagram, LANDSAT-2 Power Subsystem . . . . .5^2 

5-2 LANDSAT-2 Power Subsystem , 5.3 

5-3 LANDSAT-2 Observatory Solar Array Deployment 5-4 

5-4 Initial Acquisition of Solar Array Current 5_6 

6-1 Attitude Control Subsystem Block Diagram 6^2 

6-2 Attitude Control Subsystem , 6„3 

6-3 Separation-Acquisition Telemetry ^ ^6„7 

6-4 LANDSAT-2 Roll Rate Acquisition [ [ *6-15 

6-5 LANDSAT-2 Pitch Rate Acquisition [ [ . [ 6-16 

7-1 Narrowband Telemetry Block Diagram 7^2 

7-2 Narrowband Telemetry and Command Subsystem Block 

Diagram (Down Link) 7_3 

7-3 Narrowband Telemetry and Command Subsystem 7-4 

8-1 Command and Clock Subsystem Block Diagram 8-2 



8-2 



9-2 
9-3 



9-5 
9-6 
9-7 

10-1 



11-2 
11-3 



13^1 
13-2 



Composite STADAN Audio Waveform , . 8- 



3 



3 



9-1 Orbit Adjust Subsystem Block Diagram 9. 

Orbit Adjust Thruster Orientation ^ 9_4 

Orbit Adjust Subsystem ] ]9_5 

9-4 Performance Characteristics [9.7 

Performance Characteristics , 9^9 

Performance Characteristics 9_11 

Performance Characteristics 9^13 

MMCA Functional Block Diagram 10-1 



11-1 USBE/PMP Functional Block Diagram 11^3 

S^Band Transmission Spectrum . • ,11-4 

MSFN/USB Uplink Modulation , ! ! ]ll-5 



12-1 ERTS Observatory/Shroud Envelope and Minimum Clearances .... 12-2 

12-2 Separation and Unfold Subsystem Mechanical DetaUs .12-3 

12-3 Separation and Unfold Subsystem Functional Block Diagram 12-4 



APU Functional Block Diagram , . . . , 13-2 

PSM Functional Block Diagram ».,,.!! !l3~3 



Vlll 



LLST OF ILLUSTBATIONS (CONT^D) 

Figure Page 

14-1 Functional Block Diagram of Thermal Control Subsystem 14-2 

15-1 Narrowband Tape Recorder Block Diagram . . * * ,15-2 

16-1 Wideband Telemetry Subsystem Block Diagram 16-2 

16-2 Wideband Telemetry Subsystem 16-3 

17-1 AMS Block Diagram 17 _2 

17-2 Attitude Measurement Sensor 17-3 

18-1 WBVTR Functional Block Diagram 18-2 

18-2 WBVTR Block Diagram 18-3 

18-3 Wideband Video Tape Recorder . . . . „ 18-4 

18-4 Wideband Video Tape Recorder , 18-5 

18-5 Wideband Video Tape Recorder Transport 18-5 

19-1 Return Beam Vidicon System Functional Block Diagram 19-3 

19-2 Return Beam Vidicon 19_4 

20-1 MSS Scanning Arrangement 20-2 

20-2 Simplified Functions Block Diagram of the Overall MSS System, , , .20-3 

20-3 Multispectral Scanner. 20-4 

21-1 LANDSAT-2 Data Collection System . . . , 21-3 

21-2 Data Collection Data Flow .21-4 

21-3 Data Collection Subsystem ,21-5 



ix/x 



SECTION 1 
INTRODUCTION 



SECTION 1 
INTRODUCTION 

This document contains the results of the analysis conduqted on the telemetry data from the 
prelaunch, launch and flight activation phases of LANDS AT -2 spacecraft. It is presented by 
subsystem sections and provides for interrelationships as they exist between several sub- 
systems, A brief statement of subsystem characteristics precedes flight evaluation state- 
ments. The appendix contains a total list of components flown on LANDS AT -2 and a complete 
listing of commands and telemetry functions for reference. 

Flight data is compared to baseline data established at the 20 C plateau during thermal vacuum 
testing of the spacecraft. Evaluation guidelines were derived from the specifications developed 

from the LANDSAT program objectives, i.e. , The primary mission objective of LANDSAT-2 
is the acquisition of multi spectral images of the surface of the earth. To accomplish this 
objective, two different types of multispectral sensors are used; a three camera return beam 
vxdicon (RBV) system, and a four-channel multispectral scanner (MSS), 



A secondary objective is the use of the LANDSAT-2 receiving, frequency translating, and 
transmitting equipment as a relay system to gather data from fixed earth ^based sensor plat- 
forms which are operated by individual investigators. 

Systematic, repetitive earth coverage under nearly constant observation conditions is required 
for maximum utility of the multispectral imagery to be collected by LANDSAT-2. A circular 
sun-sjnichronous orbit provides the optimum repetitive observations conditions* 

LANDSAT -1 has been in orbit since July 23, 1972, and has its orbital parameters adjusted 
to make all descending equatorial crossings have the same sun angle, and to repeat the sub- 
vehicle earth trace every 251 orbits (18 days). LANDSAT-2 has essentially the same orbit, 
but is adjusted so that the combination of LANDSAT- 1 and LANDSAT-2 provide repeat cover- 
age of the sub-vehicle earth trace every 9 days. 

The first 50 orbits are covered in this report. 

1-1/2 



SECTION 2 
SUMMARY 



SECTION 2 
SUMMARY - ORBITS 1-50 

The LANDSAT-2 spacecraft was laiinched from the Western Test Range on 22 January 1975 at 
022:17:55:51.604. The launch and orbital injection phase of the spaceflight were nominal and 
deployment of the spacecraft followed predictions* 

POWER SUBSYSTEM (PWR) 

After separation, the solar paddles deployed successfully, slewed to proper position, and 
began normal sun tracking. The array current averaged 14.7 aikperes and reached a peak 
current of 15, 8 amperes. Battery voltages were 33.2 VDC at max charge, and the end-of- 
night voltages were about 28.6 VDC. Battery temperatures averaged 19. O^C. All compen- 
sation and auxiliary loads completed checkout successfully. In Orbit 2 the shunt loads drew 
current, showing that the automatic shimt dissipators were operable. 

ATTITUDE CONTROL SUBSYSTEM (ACS) 

Following a nominal separation at 18:54:55 and subsequent stabilization, the ACS continued 
to operate normally. Roll, pitch, and yaw position and rates specification were met success- 
fully. Existing levels of spacecraft disturbance torques resulted in an average of 1-2 gates 
of +R and 0-1 gates +P polarities per orbit. Analyses are continuing to evaluate the nature 
of the disturbances and to define subsequent compensation via the use of the Magnetic Moment 
Compensating Assembly (MMCA). The yaw mode was commanded to "normal" during inter- 
rogation 1 Alaska, 

The overall performance of the ACS has been excellent. 

COMMAND/CLOCK SUBSYSTEM (CMD) 

AU command functiojis have performed well. From separation of the spacecraft, real time, 
COMSTOR and EC AM commands have been executed in a timely and exact manner. All 

2-1 



difficulties associated with commanding have been directly relatable to acquisition/pointing 
and non-spacecraft problems. 

TELEMETRY SUBSYSTEM (TLM) 

Normal telemetry was consistently received with both the USB and VHF down links being exer- 
cised. All functions in the telemetry matrix are normal and within expected limits. All tele- 
metry indicates that the spacecraft telemetry subsystem performance has been nominal, 

ORBIT ADJUST SUBSYSTEM (OAS) 

Health functions of the OAS were normal. In-plane orbital corrections were made by firing the 
-X and +X thrusters. The test burns on these thrusters lasted 4, 8 seconds each and the longest 
burns were of 420 seconds duration. All operations were normal. Tracking data have con- 
firmed the desired corrections. About 6.69 pounds of hydrazine were used during these 
maneuvers. 

MAGNETIC MOMENT COMPENSATING ASSEMBLY (MMCA) 

Telemetry function 4002 was defective prior to laimch. Other health functions of the MMCA 
were normal. The unit was not activated during the period of this report. Insertion of dipole 
values was deferred pending evaluation of the ACS performance. ACS gating during this period 
has averaged less than one gate in the +R, -R and +P direction per orbit. 

UNinED "S" BAND/PREMODULATION PROCESSOR (USEE) 

The USEE functioned normally throughout this period. Carrier and subcarrler frequencies and 
formats were present for commands, telemetry, (1 kb real time and 24 kb playback) ranging, 
and data collection system transmissions. Power output was nominal. 



2-2 



SEPARATION AND UNFOLD SUBSYSTEM (SUS) 

The separatton subsystem performed as expected. The 2.5 second timer Initiated paddle 
unfold. Before separation the subsystem properly restrained the paddles, disabled the 
primary and redundant matrix A drivers, provided -24.5 VDC to the Attitude Control reset 
line, and provided telemetry signals indicating that the spacecraft was still mated to the Delta 
Vehicle. After separation all circuits were activated, separation was confirmed, and paddles 
were deployed properly. Both separation switches closed as expected. 

THERMAL SUBSYSTEM (THM) 

The operation of the thermal subsystem in both the sensory ring and the ACS was within the 
expected limits at aU locations. Average temperatures were: ACS baseplate 20. 5 C, 
sensoiy ring 18. 9°C, and center section 19*3^C, The shutter position average at Orbit 50 
was 42.8*^. 

ELECTRICAL INTERFACE SUBSYSTEM (EIS) 

All EIS functions that were exercised during launch and activation were executed and con- 
firmed. After launch, power switching was held to a minimum. Operation of time code 
processing, search track data processing, back-up timer operation, signal switching, and 
power switching was confirmed, 

NARROWBAND TAPE RECORDERS (NBTR) 

Both NBTR^s operated in a nominal manner. Both recorders were ON and recording during 
the launch phase. NBTR-1 was played back over Alaska in orbit 1. During orbit 2, both 
NBTR'l and 2 were played back. Data was satisfactory and continued to be normal throughout 
this report period. Telemetry points on the recorders were normal. 



2-3 



WIDEBAND TELEMETRY SUBSYSTEM (WBTS) 

Both WB links were activated during Orbit 12 in the 10 watt mode. All subsystem telemetry 
data was normal. The high power mode (20 watts) was tested in Orbit 13, and all telemetry,, 
was normal. Carrier-to-noise ratio in the wideband ground receiver IF was measured as a 
function of satellite elevation angle and checked against the RF link budget. Both links agreed 
within 2 dB with calculated performance, and link margins appear more than adequate for all 
RBV and MSS data, Prelaunch RBV and MSB data were played back over the wideband links 
in Orbit 15, and all data appeared normal, MSS minor frame sync errors measured were 
the same as measured prior to launch. (5 errors per 10 seconds at Goldstone), Both wide- 
band RF links, including receiving site equipment, performed as predicted throughout this 
period* 

ATTITUDE MEASUREMENT SENSOR (AMS) 

The AMS power was applied during Orbit 6, and the unit has performed as e3q)ected since then. 
ACS fine control agrees with AMS output, 

WIDEBAND VIDEO TAPE RECORDERS (WBVTR) 

Both recorders were OFF and at mid-tape position during launch. During Orbit 5, the re- 
corders were rewound in preparation for playing back of data recorded prior to launch* 

In Orbit 15, prelaunch RBV data from WBVTRl and MSS data from WBVTR2 were played 
back, and all data was good* MSS Sun Cal data was recorded on WBVTR2 in Orbit 21 and 
playbacks of prelaunch recorded data was made on both WBVTR's. WBVTR2 telemetry 
values and MFSE counts were nominal. 



2-4 



RETURN BEAM VIDICON (RBV) 

The RBV subsystem was activated over Greenbelt during Orbits 40 and 41, All cameras 
were turned on, each operating separately and then all together. Telemetry values and 
MPSE counts were nominal. 

The RBV was not operated again during this report period. 

MULTI -SPECTRAL SCANNER (MSS) 

The MSS was activated over Goldstone during Orbit 19. All operations were nominal. Dur- 
ing Orbit 21, a sun cal occurred over Alaska, Subsequent to activation the MSS scanned 
54 R/T scenes (185 KM x 185 KM) through Orbit 50, each consisting of images from 4 
spectral bands obtained from the United States. 

DATA COLLECTION SYSTEM (DCS) 

The DCS receiver was powered during Orbit 5, and the DCS system received and re -trans- 
mitted the normal number of messages. Telemetry was nominal. 



2-5/6 



SECTION 3 

SPACECRAFT ACTIVATION SEQUENCE 



SECTION 3 
SPACECRAFT ACTIVATION SEQUENCE 

The following paragraphs describe the activation sequence for the Spacecraft through Orbit 
50. This sequence is subdivided by orbit and interrogation. For each interrogation, the 
stations and activities are listed* Only initial activations with associated times are shown. 
All subsequent commanding was normal. 

Prelaunch (WTR, QCC) 

1. Start NBTE2 in record at 17:23:51 GMT 

2. Start NBTRl in record at 17:28:37 GMT 

3. Switch to internal power at 17:42:00 GMT 

Orbit O/l (WTR, WINKFJELD, TAN, MAD. UUV, HAW) 

1. Lift off at 022:17:55:51, 604 

2 . Separation at 18 :54 :55 

3. Ascending Node 18:57:12 

4. Confirmed Controls Stabilization of S/C, 18:56:01 

5. Satellite Night to Day Transition 19:17:03 

6. Enable USB Transmitters 18:57:36 

7. Established Command Ability 19:10:02 

8. USB Ranging ON 19:11:27 

9. Playback of NBTRl 19:26:00 

10. RMP-A, Low Motor Voltage 19:34:51 



3-1 



Orbit 2 (MAD. ULA. HAW. ACN) 

1. Confirmed ability to turn auxiliary and compensation loads on and off. 21:05:53 

2. Playback of NBTR2. 21:06:58 

Orbit 3 (MAD. ULA. GWM) 

1. Verified spacecraft status, stored and real time command capability. 
Orbit 4 fENT. ULA. GWM) 

1, Verified spacecraft status, stored aM real time command capability. 
O rbit 5 (ENT. ULA) 

1. Wideband Video-2 Recorder ON 01:59:08 

2. Wideband Video-1 Recorder ON 01:59:15 

3. WBVTR-2 Rewind 01:59:22 

4. WBVTR-1 Rewind 01:59:22 

5. WBVTR-2 OFF 02:01:20 

6. WBVTR-1 OFF 02:01:21 

7. DCS Receiver-l ON 02:02:08 

Orbit 6 ffiNT. GDS. ULA) 

1. Attitude Measurement Sensor ON 03:51:44 
Orbit 7 fGDS. ULA) 

1. Verified spacecraft status and command capabilily 
3-2 



Orbit 8 (HAW, ULA) 

1, Verified spacecraft status and command capability 
Orbit 9 (HAW, ULA) 

1. Verified spacecraft status and command capability 
Orbit 10 (MAD, ACN. GWM) 

1, Verified spacecraft status and commajid capability 
Orbit 11 (BDA) 

1, Verified spacecraft status and command capability 
Orbit 12 (ENT, ULA) 

1, Wideband power amplifiers 1 and 2 ON 10 watts (no modulation) 14:29:31, OFF 14:36:53 

2. Wideband frequency modulator inverter, ON 14:29:41, OFF 14:36:55 

Orbit 13 (ENT, EGD) 

1, Wideband power amplifier- 1 QN 20 watts (no modulation) 16: 10:39, OFF 16:17:55 

2. Wideband power amplifier -2 ON 20 watts (no modulation) 16:10:37, OFF 16:17:53 

^bit 14 (ULA, EGD) 



1. Enabled and configured RBV/MSS filters. Real time RBV data on filter A and real 
time 2 MSS data on filter B 17:56:28 



3-3 



2. Wideband power amplifiers 1 and 2 ON 17:58:37 , 20 watts. (WBPA reduced to 10 
watts 18:06:23 - no modulation 

3. WBPA's OFF 18:05:55 
Orbit 15 (ULA) 

1. WBVTR-1 Playback mode ON 19:32:06, OFF 19:51:44 

2. WBVTR-2 Playback mode ON 19:34:20, OFF 19:51:44 

Orbit 16 (ULA. MAD. HAW) 

1. Verified spacecraft status and command capability 
Orbit 17 (ACN. MAD. ULA. GWMl 

1. Verified spacecraft status and command capability 
Orbit 18 (GWM. ENT. ULA) 

1. Verified spacecraft status and command capability 
Orbit 19 (MIL. ENT. ULA) 

1. Commanded MSS band and modes ON/OFF in sequence, then total system operated 
(including WBVTR-2 Rec) 02:15:12. 

Orbit 20 (GDS. ULA. ENT) 

1. Verified spacecraft status and command capability 



3-4 



!■ 



Orbit 21 fGDS. ULA> 

1. MSS System ON 05:38:44, Sun cal performed (WBVTR-2, ON; WBPA-2, ON) 
Orbit 22 gJLA. HAW) 

1. Verified spacecraft status and command capability 
Orbit 23 fHAW. ULA. MAD. ACN. GWM) 

1. Verified spacecraft status and command capability 
Orbit 24 MAD. ACN. GWM) 

1. Verified spacecraft status and command capability 
Orbit 25 (BDA) 

1. Verified spacecraft status and command capability 
Orbit 26 (ENT. MIL) 

1. Real time MSS operations 
Orbit 27 (ENT. GPS) 

1. Real time MSS operations 
Orbit 28 (ULA. GDS) 

1. Real time MSS operations 



3-5 



Orbit 29 (ULA, MAD. HAW) 

1, Real time MSS operations 

2. KCAM activated in the Load mode and Program mode 

Orbit 30 qviAD, ULA, HAW, ACN) 

1. ECAM A and load B 
Orbit 31 (MAD. ULA. GWM) 

lo Routine operations 
Orbit 32 fENT, ULA. GWM) 

1. Orbit adjust - X thruster test at 00:34:00, 8 
Orbit 33 thru 39 

1* Routine operations 
Orbit 40 (ENT. BDA) 

1. RBV initial turn ON- OFF 
Orbit 41 {ENT, EGD) 

1. RBV test on each camera and on all 
Orbit 42 thru Orbit 44 

!• Routine operations 
3-6 



Orbit 45 (MAD. ULA. GWM) 

1. Switched to MSFN-B/STADAN A. USB-B and VHF-A now being used 
Orbit 46 (ENT. ULA. GWM) 

1. Routine operations 
Orbit 47 (MIL. ENT. ULA) 

1, Sun cal, MSS 
Orbits 48 thru Orbit 50 

1, Routine operations 



3-7/8 



SECTION 4 
ORBITAL PARAMETERS 



SECTION 4 
ORBITAL PARAMETERS 

The LANDSAT^2 spacecraft was launched from the Western Test Range in a Near Polar Orbit 
on 22 January 1975 at 17:55:51, 604 z. The official international designation is 1975-4A and 
the mission tracking and telemetry number is 7500401. 

Following are the Brouwer mean orbital elements for satellite 1975-4A (LANDSAT-2) com- 
puted and issued by the Goddard Space Flight Center. 



Table 4-1* Elements of the Mission Orbit 



1. Apogee 

2. Perigee 

3. Inclination 

4. Semi-major axis 

5. Eccentricity 

6. Anomalistic Period 

7. Distance between ad- 
jacent ground tracks 
at the equator 

8. Average cycle 
duration 

9. Delta days in 
standard cycle 
(LANDSAT-1 and 
LANDSAT-2) 

10. Phasing between 
LANDSAT-1 and"2 



Planned 



907,7 km 
907,7 km 
99, 098* deg 
7285,820* km 
0. 0001* 
103, 152 min 



159.375 km 
18 days 



9 
135-225^ 



Post Launch 



J 



915. 03 km 
901, 56 km 
99. 095 deg 

7286. 462 km 
0. 000925 
103. 165 min 



165. 57 km 
18 days 

12 
131. 9° 



J 



Post Orbit 

Adjusts^ 



916. 84 km 
898.47 km 
99. 096 deg 
7285.820 km 
0, 001260 
103. 1514 min 



159.35 km 
18 days 

9 



196.6 



*Ttie 3-sigma uncertainties for the inclination, semimajor axis, and eccentricity are +0, 1 
deg, +22,2 or -24. 1 km and 0.002 respectively. ~ ' 

1 EPOCH 75 Y 01 m 250 at 00 hrs 34. 00 min. U. T. 

2 EPOCH 75 Y 02 m 060 at 22 hrs 36, 00 min. U, T. 



The mission requirement for LANDSAT-2 was to place the satellite in a sun synchronous orbit 
with 18 day ground track repeat cycle, and to phase it at an angle of 135 to 225° with LANDSAT-1. 



4-1 



Also required was a combined full coverage of the earth, using both LANDSAT-1 and LANDSAT-2, 
in 9 days. These requirements have been achieved satisfactorily with in-plane orbital cor- 
rections of LANDSAT-2 which placed the satellites 9 days apart in the 18 day ground track 
repeat cycle. 

Figure 4-1 shows the first and subsequent orbit tracks of LANDSAT-2. All descending eq- 
uatorial crossings occur at approximately 9:30 a. m. local time. All ascending crossings are 
in local darkness. 



4-2 



^10 ,T^ I . ■.: ,,0 ,» ,0 .. .,. ,,, ,p „ ,, , , „, ,^ ,, ,, , ^„ ,^ ,„ ^^ ^^ ^^ ^ _^^ ^^ ^^ ^^ ^^ ^^ .. « . s ^ .i « „ ^ „ ,0 ., w « 



ij^ i«j ii« iM nr ito Its im iTi II D 



S 

§ 



si 




«: ^ 't *<^ lii: lii i<: <ti jo 3' 



,^ .J. .:■ .. ,s ,. .,, :^ ,, »o -. i. .. r, .,«!,« ,1 ,. „ „ „ ;, ~i .u , , . ,, ., ,. ^S « 3. «, .. « ^. M, *^ r, ,: ,o B. « ,. ,c. „, .,c ,^ ,„ .. .3. .s ... ^ <iO i« 



I6D i» 170 IF» IH 



r 

CO 



Fig^e 4-1. Subsatellite Plot of the LANDSAT-2 Spacecraft 



SECTION 5 
POWER SUBSYSTEM 



SECTION 5 



POWER SUBSYSTEM 



The power subsystem includes two solar array platform assemblies to convert solar energy 
to electrical energy; eight storage modules to store electrical energy; one auxiliary load con- 
troller and two axixiliary load panels to dissipate excess electrical power; one power control 
module and one pay load regulator module to regulate and distribute power. See Figure 5-1 
for functional block diagram,and Figure 5-2 and Figure 5-3 for hardware illustration. 



The power subsystem provides unregulated and regulated power to satisfy the electrical load 
requirements of the space craf to Unregulated power is supplied Avith a voltage range of -26 
vdc to -37. 5 vdc. The regulated power bus Is -24, 5 + 0. 5 vdc with an output dc impedance of 
0* 01 ohm and an output a:^ impedance of 0. 1 ohm at frequencies up to 10 KHz, The power 
control module can deliver up to 20 amperes and the payload regulator modide can deliver up 
to 26 amperes under these conditions^ 

The Power Subsystem was launched in the configuration shown in Table 5-1, 



Table 5-1, Power Subsystem Launch Configuration 



BATT 1 


MODE 


CMD 


SHUNT T,n D 


MODE 


CMD 






ON 


437 


BATT 2 J 






COMP T,D 1 






BATT 3 1 






CQMP LD 2 \ 






BATT 4 { 
BATT 5 / 


ON 


353 


COMP T,n 3 1 
COMP T,n 4 \ 


OFF 


355 


BATT 6 1 






COMP T,D 5 / 






BATT 7 I 






COMP T,n 6 \ 






BATT 8 






COMP T-n 7 1 






AUX LD 1 \ 






COMP T,r) 8 "^ 






AUX LD 2 / 


OFF 


374 


TR CHARGE 


NORM 


346 


AUX LD 3 > 


PRM 


ON 


727 


AUX LD 4 1 






PRM FTAP 


ON 


622 


AUX LD 5 ^ 






PSM BUSS 


EN 


655 


SHUNT LD A^ 






SW TMP PWR 


ON 


614 


SHUNT LD Bj 


ON 


437 


SPACECRAFT 


REG 1 


SEL 


SHUNT LD c) 






PAYLOAD 


REGS 


SEL 



5-1 



to 






SOLAR ARRAY 



-O^ 



501 
PLAT- 
FORM 
ASSY 



502 

PLAT 
FORM 
ASSY 



3 



tn 



STORAGE MODULE (SM) 
OF 8) 






^ 



CHARGE 
CONTROLLER 



FROM 
PCM 




r^ri 



SD 

PASS 

ELEMENT 



I :„_ 



1 



FUSE 
_ BLOW 
- TAP 



I 



TO SHUNT LOADS 

NOTE: ALL RETURNS 
CONNECTED TO S/C 
UNIPOINT GROUND 




POWER CONTROL MODULE (PCM) 
SOLAR ARRAY BUS 



AUX LOAD 
CONTROLLER 



SHUNT DISS 
DRIVER 



TO SM(8I 



UN REG BUS LOADS 



UNREG 
BUS 



PWM 
REG 



Lj I 



24.5 REG BUS 




POWER SWITCHING MODULE (PSM) 
■Kl- 



<T 



"1 



i SHUNT AUX 5 
J LOADS LOADS k 
\ (4 PR) (5) \ 

■I__.___; 



TO SD PASS 
ELEMENT 

IN SM 



AUX LOAD 
PANELS (2) 



FROM SM 



1 



AUX 
LOAD 



SHUNT 
LOAD 



_J 



— * 



I :j 



UNFOLD TIMER "^ 
-^« U* 



PULSE 
LOAD BUS 



^TO RBV SHUTTERS 
= MSS SCAN DRIVE 



TO 

PADDLE 
UNFOLD 
PYRO 



(8) 



-w— «^^<»| 

-W— KH ! , 



PWM REG n 



! 



V 



' I 



AGE 



~^ M PWM R 



EG 



(/VYVV(|, 



'24.5 REG BUS 



TO PSM 



L^. 



PAYLOAD REGULATOR MODULE 



Figure 5-1, Functional Block Diagram, LANDSAT-2 Power Subsystem 



^£3 



1^ 




POWER SWITCHING MODULE 



I 

Ca3 



Figure 5-2. LANDSAT-2 Power Subsystem 




Figure 5-3. LANDS AT -2 Observatory Solar Array Deployment 

Performance 

The battery packs in the LANDSAT-2 power subsystem were on low level charge until 
17:42:00 GMT when the spacecraft was switched to internal power prior to launch. The 
batteries powered the spacecraft for approximately one hour and 40 minutes until 19:21 
GMT when the solar array current became high enough to supply the load and begin recharg- 
ing the batteries , The maximum depth of discharge was 30. 3%, The voltage was 29, 6 at 
this point with a current of less than 50 milliamperes* 



5-4 



^fGlNAL PAGE IB 
OF POOR QUALnY 



.; • 



For comparison to LANDSAT-1 data, a time of 19:09:35 GMT was taken when the battery 
voltages were near their minimum voltage due to high currents and deep discharge. Table 
5-2 shows this comparison. The higher current shows that the LANDSAT-2 data would 
have slightly higher voltages than LANDSAT-1 data if adjusted to the same conditions. The 
voltages are quite adequate to safely supply the LANDSAT-2 mission. 

Table 5-2. Comparison of Battery Discharge Characteristics 



Spacecraft 


Current 
Spread 
(Amperes) 


Depth 
of 
Discharge 
(%) 


Voltage 
Average 
(Volts) 


Temperature 
Range 
(DGC) 


LANDSAT-1 
LANDSAT-2 


0.72-0.82 
0.89-1.00 


27.8 
27.8 


28.21 
28.29 


18. 8-21. 5 
16. 1-20. 3 



End of night voltages, average battery temperatures, and temperature spread between bat- 
teries is shown in Table 5-3. Battery performance is normal. 

The solar drives were launched with both panels in the normal mode. After deployment at 
night the right solar panel began slewing to align itself normal to the sun (see Figure 5-4). 
The left panel sun sensor did not clear the albedo shield until approximately 7 minutes into 
day one at which time it also began slewing to align itself to the sun. Final alignment to 
the sun was not complete until near the end day in Orbit 2. Orbit 3 shows the normal solar 
array signature with its two shadow areas resulting from the sensory ring shadow on the right 
panel near sunrise and sunset; and earthshine impllnging on the panels when they are jointly 
receiving direct energy from the sun and reflected sun energy from the earth. At midday 
there is no earthshine and the solar array had a current of 15. 37^ at an unregulated bus volt- 
age of 31. 9 volts. This point will be used to monitor solar array degradation in future re- 
ports. The Solar Array Average Energy was 1123 ampere-minutes in early orbits. Based 
on the above results the power subsystem is anticipated to fully support LANDSAT-2 mission 
with adequate power. 



5-5 



SHADOW 
S/C TO 
PANEL 



EARTH SHINE 

COrn-RlBUTION 



I SHADOW 

S/C TO 
PANELS 



U 
q: 

UJ 

a. 

E 

< 



UJ 

a: 
o: 

D 
O 

>- 
< 

a: 

IT 

< 

a: 
< 




fe 9- 



17^30 18.00 18.30 



19,00 19,30 20,00 20,30 21,00 2t,30 22,00 22,30 23,00 23,30 24r00 
GREENWICH MEAT TIME (HOURS, MINUTES) 



Figure 5-4. Initial Acquisition of Solar Array Current 

During Orbit 7 the shunt limiter went into operation when battery taper began. The maximum 
unregualted bus voltage during shimt limiter operation was 37,4 volts which indicates that 
the solar array bus voltage was being held at approximately 38. volts since it is a diode 
drop away. This is within the voltage specijacation of 38. + 0, 150 volts. 

The auxiliary loads and compensation load command capability were verified in Orbit 2. 
In Orbit 2 compensation loads 1, 2, 3, 4, 5, 7 and 8 were turned on as scheduled to pro- 
vide more even heating of the spacecraft until normal operation began. All compensation 
loads except 6 remained on thru Orbit 50. 



5-6 



Auxiliary loads were not required during Orbit 1, to allow a preplanned overcharge to be 
given to the batteries. In Orbit 2 auxiliary loads 1, 2, 3, 4 were turned on as scheduled 
by power management. Normal auxiliary load programming proceeded as planned by 
power management in subsequent orbits. 

Table 5-3 shows major power subsystem parameters and Table 5-4 shows power subsystem 
telemetry for selected orbits. All regulated voltages are stable and in close agreement 
with ground measurements. Some parameters in Table 5-4 may be slightly different than 
Table 5-3 because 5-3 uses a time span for power management (night followed by a day) 
different from the time span which is used in Table 5 --4 which is the playback period from 
the NBTR. 



5-7 



Table 5-3. LANDSAT-2 Major Power Subsystem Parameters 



°*«» 



Pwr. Mgmt, Orbit No. 


2 


7 


26 


50 


Batt 1 M^ 


32*05 


33.85 


33.51 


33,43 


2 Chge 


31.95 


33.91 


33.40 


33.40 


3 Volt 


31.98 


34,03 


33.43 


33.35 


4 


32.00 


33. 79 


33.54 


33.45 


5 


31.96 


33.68 


33,43 


33,42 


6 


32.05 


33.67 


33.50 


33.41 


7 


31,99 


33.79 


33.54 


33.45 


a 


31.99 


33.70 


33.53 


33,45 


Average 


32.00 


33.80 


33,43 


33.42 


Batt 1 End-of-Nlght 


20.32 


29,32 


29.49 


29,32 


2 Volt 


29.38 


29.29 


29,46 


29,38 


3 


20.32 


29.32 


29,49 


29,32 


4 


29.34 


29.34 


29.52 


29.34 


5 


29.40 


29.40 


29,43 


29.40 


6 


29.31 


29,31 


29,43 


29,31 


7 


29.34 


29.42 


29.51 


29.34 


8 


29.34 


29.34 


29,61 


29,34 


Average 


20,34 


29,34 


29.49 


29.34 


Batt 1 Chge 


12.07 


12,26 


12.50 


12.76 


2 Share 


11.75 


12.14 


11,89 


11,68 


. 3{%> 


12.60 


13.81 


12,41 


12.24 


4 


12.28 


12.20 


12.10 


11.99 


5 


13.02 


12,89 


12.84 


13,34 


6 


13,15 


13.09 


13.31 


13.35 


7 


12.69 


12,77 


12,65 


12,90 


8 


12.43 


11.84 


12,09 


12,24 


Batt 1 Load 


12.14 


12,20 


12.60 


12,60 


2 Share 


12.62 


12,81 


12.69 


12.70 


3(%) 


13,06 


13,07 


12.77 


12.67 


4 


12.64 


12,50 


12,47 


12,44 


5 


12.29 


12.38 


12.40 


12.34 


6 


12,49 


12.80 


12.61 


12.70 


7 


12.40 


12,48 


12.39 


12,47 


8 


12.35 


11.75 


11.96 


12.04 


Batt 1 Temp 


17.39 


13,63 


19,66 


21.46 


2 In 


17,60 


13,83 


19.53 


20.25 


3 (OC) 


16.51 


17.20 


17.97 


18.60 


4 


18.08 


20.04 


20.73 


20.83 


5 


21.80 


22,94 


24,33 


24,98 


6 


20.80 


21.92 


23.23 


24.26 


7 


20.59 


22,14 


23,54 


24.71 


3 


19.78 


21,09 


22.21 


23.63 


Average 


19,07 


20.36 


21.43 


22,34 


S/C Reg Bus Pwr, (W) 










Comp Load Pwr. (W) 










{P/O S/C Reg Bus Pwr) 










P/L Reg Bus Pwr. (W) 










C/D Ratio 


1,09 


1*21 


1,13 


1.15 


Total Charge (A-M) 


197,4 


230.6 


256.3 


271.9 


Total Discharge (A-M J 


181,5 


232.6 


226,0 


237.2 


Solar Array (A-M) 


1106 


1096 


1110 


1106 


S. A, Peak 1 (Amp) 


16,15 


16,05 


16.35 


16,05 


Sun Angle peg) 










Max R Pad Temp (^C) 










Min R Pad Temp fC) 










Max L Pad Temp (^C) 










Min L Pad Temp ^C) 











5-8 



Table 5-4. LANDSAT 2 Power Subsystem Analog Telemetry 
(Average Value for Data Received in NBTR Playback) 



Function 



Description 



Unit 



T/V* 


Orbits 
3 


50 


** 


0.87 


1.01 


** 


0.88 


1.01 


** 


0.89 


1.00 


** 


0.86 


1.00 


** 


0,88 


0.99 


** 


0.93 


1.02 


** 


0.88 


1.00 


** 


0.86 


0.97 


** 


0.34 


0.47 


** 


0.33 


0.43 


** 


0.36 


0.45 


** 


0.35 


0.44 


** 


0.37 


0.47 


** 


0.37 


0.49 


** 


0.36 


0.47 


** 


0.36 


0.45 


** 


30.69 


31.50 


** 


30.67 


31.48 


++ 


30.68 


31.49 


*+ 


30.68 


31.49 


** 


30.69 


■31. 50 


** 


30.69 


31.49 


** 


30.71 


31.52 


** 


30.68 


31.49 


** 


17.41 


21.59 


** 


17.53 


20.53 


** 


16.28 


18.80 


** 


18.17 


20.90 



6001 


Batt 1 Disc I 


6002 


2 


6003 


3 


6004 


4 


6005 


5 


6006 


6 


6007 


7 


6008 


8 


6011 


Batt 1 Chg I 


6012 


2 


6013 


3 


6014 


4 


6015 


5 


6016 


6 


6017 


7 


6018 


8 


6021 


Batt 1 Volt 


6022 


2 


6023 


3 


6024 


4 


6025 


5 


6026 


6 


6027 


7 


6028 


8 


6031 


Batt 1 Temp 


6032 


2 


6033 


3 


6034 


4 



Amp 



Amp 



VDC 



DGC 



5-9 



Table 5-4. LANDSAT 2 Power Subsystem Analog Telemetry (Cont'd) 
(Average Value for Data Received In NBTR Playback) 






or p;::^^^ Page ^ 



AUfy 



Function 


Description 


Unit 


Orbits 


T/V* 


3 


50 


6035 


5 




+♦ 


21.85 


25.16 


6036 


6 




** 


20.74 


24.37 


6037 


7 




+* 


20,50 


24.83 


6038 


8 




** 


19,79 


23.75 


6040 


Rt. Pad Temp 


DGC 


** 


29,59 


28.96 


6041 


Bt Pad VM 


VDC 


*+ 


32.82 


33,72 


6042 


Rt. PadVN 


VDC 


** 


32.52 


33,46 


6044 


Lt. Pad Temp 


DGC 


** 


26.51 


25.56 


6045 


Lt. PadVF 


VDC 


** 


33.45 


34.40 


6046 


Lt. Pad VG 


VDC 


♦♦ 


33.54 


34.48 


6050 


S/C UH Bus V 


VDC 


*+ 


30.86 


31,73 


6051 


S/C RG Bus V 


VDC 


24.56 


24.54 


24.57 


6052 


Aux Reg AV 


VDC 


23.36 


23.35 


23,36 


6053 


Aux Reg BV 


. VDC 


23.35 


23.35 


23,37 


6054 


Solar I 


Amp 


*♦ 


14.95 


14.81 


6055 


S/C RG Bus I 


Amp 


+* 


6.83 


+** 


6056 


S/C RG Bus I 


Amp 


** 


6,84 


7.23 


6058 


PC Mod Tl 


DGC 


*♦ 


18.70 


21,67 


6059 


PC Mod T2 


DGC 


♦* 


17.80 


20,44 


6070 


P/L RG Bus V 


VDC 


24.60 


24.57 


24,61 


6071 


P/L UR Bub V 


VDC 


** 


30; 90 


31.85 


6072 


P/L RG Bus I 


Amp 


*+ 


0.41 


*** 


6073 


P Aux AV 


VDC 


23,51 


23.46 


23.47 


6074 


P AuxBV 


VDC 


23.48 


23.43 


23.46 


6075 


PRModTl 


DGC 


** 


18,60 


20.84 


6076 


PR Mod T2 


DGC 


** 


20.28 


22.13 


6079 


Fuse Blow V 


VDC 


** 


24.45 


24,48 


6080 


Shunt 1 I 


Amp 


** 


0.0 


0,0 


6081 


2 




** 


0,0 


0.0 


6082 


3 




♦♦ 


0.0 


0.0 


6083 


4 




** 


0.0 


0.0 


6084 


5 




** 


0.0 


0.0 


6085 


6 




♦* 


0.0 


0.0 


6086 


7 




♦* 


0.0 


0.0 


6087 


8 




** 


0,0 


0,0 


6100 


P/L BG Bus I 


Amp 


*♦ 


0,41 


0.38 


Total No, 


Major Frames 


Frm 


** 


369 


396 



*T/V <20"C) 
**Data £com T/V not applicable 



5-10 



SECTION 6 
ATTITUDE CONTROL SUBSYSTEM 



SEC1TON6 
ATTITUDE CONTROL SUBSYSTEM 



The Attitude Control Subsystem {ACS) consists of 13 major component parts, plus a thermal 
subsystem mounted to a structure composed of mounting surfaces above a honeycomb base- 
plate. Solar paddles are attached to two separate shafts, with individual drive motors to 
provide greater reliability in solar tracking* 

The major requirement of the ACS is to provide satellite alignment with the local earth 
vertical and orbit velocity to within + 0,7 degree in pitch and roll and + 1 degree in yaw* 
The instantaneous angular rates about the axes during normal operation are required to 
be less than . 10 degree/second. 

To accomplish this, a 3-axis active ACS is provided, using horizon scanners for roll and 
pitch attitude error sensing, and a rate gyro used in a gyro-compassing mode to sense yaw 
attitude. Included also is a yaw rate gyro to sense yaw rate in an acquisition mode* The 
torquing subsystem uses a combination of reaction jets to provide net momentum control 
and large control torques when required. Flywheels are utilized for fine control and 
residual momentum storage* See Figure 6-1 for the ACS functional block diagram, and 
Figure 6-2 for the hardware configuration* 

The ACS subsystem was launched in the mode shown in Table 6-1, 

LANDS AT-2 was launched from the Western Test Rapge on 22 January 1975 at 17:55:51 
hours GMT. 

During the orbit insertion - preseparation phase of the launch activity - ACS telemetry 
received after shroud ejection indicated a normal ride with all ACS systems functioning 
properly* 



6-1 



to 



9S 




TELEMETRY 










. ijrt 


r 


PULSE 

MODULATOR 




k. 


PNEUMATICS 






'\ 


























LEAD LAG 






TIME ENABLED 

MOMEISTTUM 

UNLOAD 


TACHOMETER 
















PFTCH 










1 


HORIZON 
SCANNERS (Z) 




ATTITUDE 
COMPUTER 










PULSE 

MODULATOR 


REACTION 
WHEEL 




ROLL 




' 






























i 




LEAD LAG 


u^ 


=\ h 


PULSE 
MODULATOR 


PNEUMATICS 






* 


? 




' 


























TIME ENABLED 

MOMENTUM 

UNLOAD 










( 

^ 










TACHOMETER 








1 


REACTION WHEEL 
SCANNER 








i 


L 




. 








RADIOMETRIC tNPUT 










' 
^ h 










LEAD LAG 


J 


PULSE 
MODULATOR 


REACTION 










-v^ 


^ * 




^ 


WHEEL SCANNER 



YAW RATE 
GYRO 




PULSE 

MODULATOR 



# PNEUMATICS 



YAW 
GYROCOMPASS 



YAW 
GYROCOMPASS 



YAW BIAS 






V- 


MOMENTUM 
UNLOAD 


id 






1 






TACHOMETER 






iL 


LEAD LAG 


PULSE 
MODULATOR 


REACTION 
WHEEL 









Figure 6-1* Attitude Control Subsystem Block Diagram 










I 

€0 



Figure 6-2. Attitude Control Subsystem 



Table 6-1. Attitude Control Subsystem Launch Mode 



ACS 


Subsystem 


Cmd 


Verification (Event No. ) 


LO VOLT INT 


RESET 


044 


Pneumatics Enable (164) 


BSAD HATE 


NORM 


425 


SAD Right Rate - Normal (178) 


LSAD RATE 


NORM 


244 


SAD Left Rate - Normal (176) 


RSAD RATE 


EN 


311 


Right SAD CCW Reset, CW (177) 


LSAD RATE 


EN 


365 


Left SAD RESET CW, CCW (175) 


RSAD PWR 


FUSE 


674 


SAD Right Power - FUSD (191) 


LSAD PWR 


FUSE 


713 


SAD Left Power FUSD (190) 


PNEU 


EN 


040 


Pneimiatics - Enable (164) 


PNEU INTLK 


DIS 


042 


Pneumatics Interlock - Bypass (165) 


PMB MODE 


DIS 


104 


None 


P POS BIAS 


+ 


145 


Pitch Bias - Position (185) 


0. 6 PPB 


DIB 


663 


Pitch Bias -4.87, (1048) 


2.0 PPB 


DIS 


661 


4. 87 TMV (1048) 


2. 9 PPB 


DIS 


122 


4. 87 TMV (1048) 


P UNLOAD 


EN 


165 


Pitch - Roll Unload, Both (169) 


R UNLOAD 


EN 


161 


Pitch - Roll Unload, Both (169) 


TACH 


EN 


064 


R DFT ST - Normal (188) 


TACH GAIN 


NORM 


100 


R DFT ST - Normal (188) 


YAW WHEEL 


EN 


163 


Yaw Wheel Enable (180) 


YAW POS BIAS 


H- 


160 


Yaw Bias 6. 35 RMV (1049) 


0. 1 YPB 


DIS 


120 


Yaw Bias 6. 35 TMV (1049) 


0. 3 YPB 


DIS 


060 


Yaw Bias 6. 35 TMV (1049) 


0.6 YPB 


DIS 


623 


Yaw Bias 6. 35 TMV (1049) 


RLNA/YAW 


DIS 


102 


RLNA - Yaw - Disable (179) 


YAW MODE 


ACQ 


204 


Yaw Mode - Acquisition (162) 


0. A Mode 


DB 


221 


Orbit Adj - Disable (163) 


400 RPM INT 


EN 


203 


400 RPM - Enable (189) 


RMPB 


EN 


223 


Select RMP - No. 2 (170) 


RMP B HTR 


ON 


305 


RP2 Stat Normal (173) 


RMP B MTR 


ON 


304 


RP2 Stat Normal (173) 


RMP A MTR 


ON 






AND HTR 


ON 


307 


RMP A OFF 






271 


RMP A MOTOR START 






307 


RMP A OFF 






326 


RMP A ON 






271 


RMP A MOTOR START 
8 SEC DELAY 






326 


RMP A ON 

30 SEC DELAY 






370 


RMP A HTR ON 


ENSCANSEL 


A 


636 


Scanners Both 1 (194) 


SSM 


LOCK 


675 


Scanner - Lock (192) 



6-4 



The Delta vehicle began its pitch -up maneuver at 18:47:30 hours GMT. Qualitative attitude 
error telemetry information - roll coarse error, pitch coarse error and yaw gyro rate - 
received from LANBSAT-2 prior to rear scanner uncovering Indicate that by pitch^up com- 
pletion (18:54:00), the spacecraft was well aligned with its normal attitude coordinates (see 
Figure 6-3). 

LANDSAT-2 separated from the Delta vehicle at 22:18:54:55. Two and one half seconds later, 
the paddle unfold timer functioned on schedule and the solar paddles deployed completely. 

Seventeen and one half seconds after separation (18:55:12) the ACS was activated, and acquisi- 
tion in roll, pitch, and yaw was accomplished in a classical, textbook fashion with a minimal 
amount of ACS gas used. 

Fifty two and one-half seconds after separation the SADS were activated and both drove at 
normal bias rate during spacecraft night. 

As the spacraft entered daylight at 19:17:03, both SADS performed normally. The RSAD 
began to slew and acquire because its sun sensor was exposed; while the LSAD lagged 
behind until 19:44:30* when its sun sensor cleared the albedo shield. It began to slew and 
by 20:26:30, both SADS were in synch and aligned properly with the sun. 

Solar current was demonstrated prominently by 19:20:00. 

LANDSAT-2's first ascending node crossing occurred at 18:57:12, and by 18:59:00 the ACS 
was operating normally. 

The spacecraft was commanded into the YAW NORMAL mode at 19:10:47, and ACS PNEU- 
MATICS were disabled at 19:11:46. 

RMPA lower motor voltage was conmianded at 19:34:50. 

Day to night transition occurred at 20:31:52; the second ascending node crossing followed 
at 20:40:38 and finally, RMP A was commaned OFF at 21:14:06, during Orbit 2 Alaska. 

6-5/6 




V 



CD 

B 



CD 

B 



OFF ON 


OFF ON 


OFF ON 


OFF OFF 


OFF ON 


OFF ON 


+ 


— 


+ 


*- 


+ 


— . 


PITCH SOL 
C16R3 

F1D64 


PITCH SOL 
CI7R3 
F1065 


ROLL SOL 
Ct6R2 
FI062 


ROLL. SOL, 
Ct7R2 
F1063 


YAW SOL 
Ct6R2 
F1066 


YAW SOL 
C16R4 
Ft067 



> 

o 



§ 



15 SEC TIMER 
SO SEC T^ER 



C15R2S 

1/16 
FT 200 



C2R35 

1/16 
F1201 



FWD SCAN UPSIDE DN 
PITCH PNEU MOD 



C12R64 C13R0 
1/16 1/1 

F1006 F1044 



PITCH COARSE ^fm REAR SCAN UPSIDE DN ROLL COARSE ERR 
YRG RATE 



C7R1 

1/1 

F1040 



CT0R64 

1/16 
FI015 



C13R3 

t/1 
F1072 



C4R1 

1/» 
FtOZ9 



YAW PNEU MOD 
ROLL PNEU MOO. 



C1R28 C8R47 
1/16 1/16 
F1036 FlOZe 



RMP#1 IND RATE 
(MED) 



C6R2 
1/1 

Fiose 



RMP#2 IND RATE 
(MED) 



C9R2 

1/1 
FI096 



ACS 1 




RMP hK>. 2 JND 
SATE HI 



C7R2 
FI097 
1/1 



YAW TACH OUTPUT 
IVV RMP STATUS 



C6R1 C12R35 

F1035 P-ID49 

1/t 1/16 



ACS 2 




n 



r 



t>o 



H 


r/1 


& 




B 


I4J 
4 


(D 


P 


r+ 


r+ 




1 




> 




a 




>9 




B. 




tft 




I-*' 




r+ 




H" 




O 




tl 



ENA DIS 

400 RPM INLK 
C12R1 

FlOfi> 



ccw cw 

SAD L ^ SW 

C2R2 

F12S0 



HIGH NORM 
SAD L RATE 
C1R2 
Ft249 



CCW 
SADR 
C16R1 
FI230 



CW 
^ SW 



HIGH 

SAD R RATE 
C15RI 



NORM 



LOCK UNLOCK 
SINGLE SCAN MODE 

ClORI 
F1290 



TOC TIC 
CMD CLOCK 
C17R3 
F8057 



PITCH TACH 
SAD LEFT TACH 



CIRM C7R^ 
1/ie 1/1 

F1042 F1241 



LpFT COSINE, POT 



C6R39 

1/16 
F1293 



SAD L SUN SENSOR 
SAD LMTR WIND V 



C1BR34 C6R3 
1/16 1/1 

F1246 F1240 



SAD R TACH 
SOLAR ARRAY I 



C5R3 C1R9 

1/1 1/16 

F1221 F605d 



RIGHT COSINE POT 



C2R39 

1/16 
F1292 



SAD R SUN SENSOR 
SAD R MTRWINDV 



ceR44 C9RO 
1/16 1/1 

F1226 F1220 



RMP # 1 MTR CURR 
MANIFOLD PRESS 



RMP #2MTRCURR 
TANK PRESS 



C1SR44 C1BR7I C12R44 C1SR62 

1/16 t/16 1/16 1/16 

F1082 F1213 F1092 F1212 



ACS 4 



ACS SYSTEMS ACQUISITION TELEMETRY EVALUATION 

The ACS system functioned flawlessly during the attitude acquisition phase of launch operations 
and demonstrated its ability to rapidly acquire and maintain spacecraft normal attitude with 
a minimum number of corrective maneuvers . 

Acquisition in pitch, roll, and yaw was deemed successfully accomplished when the space- 
craft's normal attitude was oriented and maintained within the following dynamic constraints: 

PITCH & ROLL 

• Angular position error within the + 5 control deadband 

• The flywheels have captured, and control of the spacecraft is maintained via flywheel 
operation rather than pneumatics 



YAW 



The flywheel speeds are below saturation levels 

The angular position 
via flywheel activity 



The angular position error within the + .1 control deadband, can be maintained 



The angular position rates of change are equal to or below . 1 /SEC 



• The spacecraft has acquired in PITCH AND ROLL within the + 5 deadband 

• The YAW gyro is running below saturation 

• The RMP HI mode is out of saturation 

« The YAW rate is equal to or below . 25^/SEC 



6-13 



LANDSAT-2^s separation and attitude acquisition times were determined by evaluating 
the telemetry strip charts (Figure 6-3) generated during this phase of launch operations 
and then confirming the activation times of principle ACS subsystems vis the DLP 
program. 

Chronology consistent with the criteria defining spacecraft attitude acquisition is sum^ 
marized in Table 6-2, 

Table 6-2, LANDSAT 2 - Attitude Acquisition Chronology 



Acquisition Criteria 


RoU 


Pitch 


Yaw 


j; 5^ deadband control 


To 
(18:54:55) 


Tq + 28 sees 
(18:55:23) 


- 


+ .7^ deadband control 


To + 33 sees 
(18:55:28) 


To + 150 sees 
(18:57:25) 


- 


+ , 1 Vsec error rate 


T^ + 36.9 sees 
(18:55:31.9) 


To + 46 sees 
(18:55:41) 


- 


RMP^s (HI mode) out of 
saturation 


- 


- 


To + 66 sees 
(18:56:01) 


Yaw rate ^ .as^sec 


— 


— 


To + 66 sees 
(18:56:01) 


Full Acquisition 


36.9 sec 


150 sees 


150 


time of separation) 









PITCH AND ROLL ERROR RATE DETERMINATION 

Pitch and roll error rates are not telemetered functions; consequently, in order to determine 
the instants in time when the spacecraft had acquired in pitch and roll with an angular rate of 
change less than + . 1 /sec, it was necessary to employ a technique that utilized pitch and 
roll angular error telemetry, recorded as a differentialple function of time. 

Function 1041 (Pitch Fine Error) and Function 1030 (Roll Fine Error) were replotted in 
engineering units (degrees) as a function of time from points taken directly from the strip 
charts . 



6-14 



The resiilting pitch error and roll error curves were then graphically differentiated, using 
a modified mean value theorem approach* This technique provided the slope of a point on 
the error curve as a function of time. 

The slopes were plotted against the same time scale as the error curves, with each slope 
data point (ordinate) in synch with its corresponding point on the error curve. 

The resulting "rate^' curves, Figures 6-4 and 6-5 ^ then defined the times when acquisition 
occurred according to '^rate'^ criteria. 



o 

UJ 

in 
oc 

UJ 
0. 

o 
ui 

o 

iij 

< 

O 
a: 



.z 



't*- 



a 1 

UJ 

Q£ 
O 

u 

Q 

r 

o 

LJ 

liJ 

Z 

Ll 

or 



-Z 




15 



ROLL FINE ERROR-F1030-(DEG) 



-L 



20 25 30 35 

TIME FROM SEPARATION (lfl:54:55)- SECS: 



ROLL ERROR RATE (^/&EC) 



75:22:18:55:31:9 
ROLL ACQUISmON 
RATE EQUALS 
a 1 DEG PER SEC, 



(T^ + 36,9) 



40 



Figure 6-4. LANDSAT-2 Roll Rate Acquisition 



6-15 



\ 



4 r 



PITCH FINE ERROR-F1041-(DEGREES) 








0) 






UJ 






UJ 






q: 


o 

U 
0) 


1.0 


o 
r ^ 

Q 


DC 




, x 


UJ 




o 


Ql 




- q:: 


ffi 




' UJ 


UJ 


as 


, 


q: 






o 




•• 


UJ 






Q 




" 


U 




- 


H 




. 


< 






K 


n 





75:22:18:55:41 PITCH ACQUISITION RATE EQUALS 
0.1 DEG PER SEC. 



Figure 6-5. LANDS AT -2 Pitch Rate Acqmsition 



ROLL ACQUISITION EVALUATION 

Roll acquisition was accomplished with facility shortly after separation. The Delta vehicle 
assisted in this operation by pre-f 
deadband, even before separation* 



assisted in this operation by pre-positioning LANDSAT-2 almost within the + 5 control 



Figure 6-3, Roll Coarse Error, shows the roll attitude error beginning to decrease with the 

commencement of the pitch-up maneuver (T -425), Roll Fine Error shows the spacecraft 
/ o 

being oriented to near roll acquisition attitude at the completion of the pitch-up maneuver 



(T^ -55). 



Separation (T = 18:54:55 GMT) generated roll attitude perturbations, but these motions 
damped out rapidly and at ACS systems enable (T +17-5) the spacecraft was within the ± 5 



control deadband. 



Roll error continued to decrease after ACS activation and entered the +*7 control deadband 
at (T H-33) seconds. 

Roll forward flywheel speed began to increase, and one - roll gate at (T +63) was required 
to assist the flywheels in controlling roll attitude within the +. 7 deadband. 

Figure 6^4 shows the spacecraft's roll rates from activation throu^ 0. 1 /SEC roll rate 
acquisition. The curve was not extended in time beyond the 0. 1 /SEC roll rate acquisition 
point because roll fine error was approaching zero in an asymptotic manner with no rapid 
changes in slope indicated. Table 6-3 simim arizes LANDSAT 2's Roll Acquisition Chronol(^y, 



6-17 



Table 6-3. Roll Acquisition Telemetry Data 







1029 


1030 




102G 


1027 






RoU 


Roll 


* 


Roll 


Roll 






Coarse 


Fine 


RoU 


Fwd 


Rear 


Activity 


Time 


Error peg) 


Error (Deg) 


Rate peg/Sec) 


(RPM) 


(RPM) 


Separation 


To 

18:54:55 


-5.5^ 


SAT 


- 


615 


615 


Separation + 10 Sec 


To +10 
18:55:05 




-2.15^ 


- 


615 


615 


ACS Loop Enable 


To +17.5 
18:55:12.5 




-1,85 





615 


615 


+ .7^ Fine Error Dead 
Band Acquisition 


To +33 
18:55:28 




-.70^ 


+, 19VSec 


625 


923 


+. 1 VSec Roll Rate 
Dead Band 

Acquisition 


To +36. 9 
18:55:31:9 




- .32^ 


+. l7Sec 


90S 


818 


(1063) 
-RoU Sol 


To-^«3 
18:55:58 




+ .36^' 




1093 


615 


(1062) 
+R0II Sol 


To +287 
18:59:31 




+ .36^ 




1064 


615 


(1063) 
-RoU Sol 


To +295 
18:59:39 




+ .36^ 




1064 


615 



♦Calculated - See Figure 6-4 

PITCH ACQUISITION EVALUATION 

The Pitch Coarse Error and Pitch Fine Error telemetry channels shown in Figure 6-3 presents 
the chronology of LANDSAT-2'b pitch acquisition. 

A smooth and accurate pitch-up maneuver terminated with the spacecraft in an approximate 
-18.5 pitch attitude. This value is qualitative because the spacecraft's rear scanner was 
covered by the solar paddles during the pitch-up/separation operation. 

A +pitch gate occurred almost immediately after ACS loop activation at (Tq +17.5). The 
resulting impulsive torque was adequate to orient the spacecraft within the ±5*^ control 
deadband at (Tq +28), 

A -pitch gate at (T^ +32) was necessary to reduce the pitch error further and to dampen the 
spacecraft's pitch rate. 



Pitch rate acquisition occxirred at (T +46) as shown in Figure 6-5. 



6-18 



ORIGINAL PAGE IS 
Oi^ POOR QUALHY 



A final -pitch gate occurred at (T +62) and this action reduced the pitch error to within the 
+0. 7^ deadband by (T +150). 

Pitch flywheel activity was smooth and responsive during the entire pitch acquisition phase, 
and its performance since acquisition has been normal. Its wheel speeds ranged from -185 
rpm to +1170 rpm. Table 6-4 summarizes LANDS AT 2*s pitch acquisition chronology. 



Table 6 --4. Pitch Acquisition Telemetry Data 



Activity 


Time 


1040 

Pitch 

Coarse 

Error 

(Deg) 


1041 

Pitch 

Fine 

Error 

(Deg) 


* 

Pitch 
Error 
Rate 
(Deg/Sec) 


1043 

Pitch 

Flsrwheel 

Speed 

(RPM) 


Separation 


To 
18:54:55 


-18.5 


- 


- 


-10.0 

ccw 


Separation + 10 


To +10 
18:55:05 


-4.6 


- 


- 


-10.0 

cw 


ACS Loop Enable 


To +17. 5 
18:55:12.5 


-11.25 


- 


- 


-10.0 

ccw 


+ Pitch Gate (1064) 


To +18 
18:55:13 


-11.25 


- 


- 


-10.0 

ccw 


+ 5° Pitch Error 
Acquisition 


To +28 
18:55:23 


-5. 


- 




-180.0 

ccw 


- Htch Gate (1065) 


To +32 
18:55:27 


- 


-1.09 


+ .71° /Sec 


-95 

CW 


+ . 1°/Sec Error 
Rate Acquisition 


To ^6 
18:55:41 


- 


2.45 


+ . l^/Sec 


183 
CW 


- Pitch Gate (1065) 


To +62 
18:55:57 


- 


3.45 


— 


-660 
CCW 


+ . 1° Fine Error 
Acquisition 


To +150 
18:57:25 


- 


-.7 


- 


260 

CW 


- Pitch Gate (1065) 


To +282 
18:59:37 


— 


-*1 


— 


730 

CW 



*Calculated-See Figure 6-5 



6-19 



YAW ACQUISITION EVALUATION 



,0 



The yaw rate gyro remained essentially constant at -0. 0313 /sec during the acquisition phase 
of the launch activity as can be seen in Figure 6-3. 



Exceptions occurred during the following intervals: 



Activity 

• pitch-up maneuver 

• pitch-up conclusion 

• + yaw gate 

• - yaw gate 



Time 

T -198 
o 

T -55 
o 



T +20 
o 



T +27 
o 



Yaw Rate Error 
+1.453Vsec 

-.4009*^/860 

+.1754^/sec 

+. 1754^860 



The maximum yaw rate error (+0. 175^/sec) occurred after ACS activation when the yaw 
tach output reached -520 rpm and a minus yaw gate occurred (T +27). After the -yaw 
gate occurred, the yaw error rate returned to -0. 0313^/sec* The duration of each cf the 
rate perturbations was approximately 10 seconds long. The RMP's in HI rate were out of 
saturation initially at (Tq +43), however, the -pitch and -roll gates which occurred at 
(To +62) momentarily disturbed the RMP's stability and the RMP^s re-entered saturation. 
Restabilization and acquisition occurred at (Tq +66). Table 6-5 summarizes LANDSAT 2^s 
yaw acquisition chronology. 

Table 6-5. Yaw Acquisition Telemetry Data 



Activity 


Time 


1035 

Yaw 

Tach 

Output <RPM> 


1087 

RMPl 

Ind. Rate 

HI^/SEC 


1097 

RMP2 

Ind, Rate 


Separation 


To 
18:54:55 





Saturated 


Saturated 


Separation +10^ 


To 
18:55:05 





Saturated 


Saturated 


Activation 


To +17.5 
18:55:12,5 





Saturated 


Saturated 


(1066) 
+Yaw Gate 


To +20 
18:55:15 


-180 


Saturated 


Saturated 


Mas ' RPM 


To +26 
18:55;21 


-465 


Saturated 


Saturated 


(1067) 
-Yaw Gate 


T^+27 
18:55:22 


-405 


Saturated 


Saturated 


RMP'a out of 

Saturation 

(Acquisition) 


18:56:01 


+650 


. 00236 VSEC 


, 00142°/SEC 



6-20 



POST SEPARATION PERFORMANCE 

The ACS has performed well since launch. Following stabilization of the spacecraft, the 
pneumatics were disabled and pneumatic gates in pitch have occurred at a rate of ?* 1 per 
orbit. Roll gating is ^2 per orbit. Pneumatics unloading is accomplished by stored momentary 
enable commands. The commands are timed to occur In the umbra and away from the SN/SD 
and SD/SN transition. The remaining useable Impulse at the end of orbit 29 was 537. 493 lb/ sec. 

Yaw mode was commanded normal during Orbit 1 Alaska. RMP2 has been selected as the 
prime instrxmient, and has been enabled since launch. RMPl was turned off in Orbit 2, 
Alaska. 

ACS THERMAL PERFORMANCE 

Temperature and pressure have remained normal, with the forward scanner being an excep- 
tion. The forward scanner developed a leak prior to launch and has continued to leak at a 
constant rate. At the end of 40 orbits ^ the SCEST mean value pressure reading for Function 
1003 was 9.550 PSL 

ACS VOLTAGES AND CURRENTS 

All voltages and currents have been within specified limits (see Table 6-6), 

MAGNETIC MOMENT COMPENSATION 

The Magnetic Moment Compensation system was not enabled during the first 40 orbits. 

Tables 6-7 through 6-13 are offered as a summary of spacecraft performance from T/Y 
through actual in-orbit operation. 



6^21 



Table 6-6. Subsystem Temperature and Pressure Averages 



Function 



Units 



0/1 



Orbits 



T/V+ 
25**C Values 



29 



1084 RMP 1 Gyro Temperature 
1094 RMP 2 Gyro Temperature 

1222 SAD RT MTR HSNG Temp. 

1242 SAD LT MTR HSNG Temp. 

1223 SAD RT MTR WNDNG Temp. 

1243 SAD LT MTR WNDNG Temp. 
1228 SAD RT HSG Pressure 
1248 SAD LT HSG Pressure 

1007 FWD Scanner MTR Temp. 2.90 
1016 Rear Scanner MTR Temp. 2.37 
1003 FWD Scanner Pressure 
1012 Rear Scanner Pressure 

1212 Gas Tank Pressure 3,67 

1210 Gas Tank Temperature 

1213 Manifold Pressure 

1211 Manifold Temperature 

1059 CLG Power Supply Card Temp. 

1260 THOl EBP 

1261 TH02 EBP 

1262 TH03 EBP 



1263 THOl STS 


1264 TH02 STS 


1265 TH03 STS 


1266 TH04 STS 


1267 TH05 STS 


1224 SAD R FSST 


1244 SAD L FSST 



DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

PSI 

PSI 

DGC 

DGC 

PSI 

PSI 

PSI 

DGC 

PSI 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 

DGC 



* Thermal Vacuum Test Data 

(1) RMP-1 Left off after initial test in Orbit 1 

(2) Prelaunch leak - refer to text 
NA = Not Applicable 

D = Defective telemetry point 



79,64 
76,06 
27.67 
25.68 
28.82 
27.26 

7.40 

7.27 
23,10 
26.13 

9.57(^) 

6.19 
1921.8 
20,33 
66.19 
19.52 
36.50 
25.14 
23.42 
26.86 
17.28 
D 

18.84 
16.24 
16.76 
15.17 
17.89 



78.5 

78.0 

27.6 

26.7 

28.5 

26,0 

7,30 

7.25 

27.0 

29.0 

5,4 

6.86 

1270.0 

23.7 

71.7 

20,5 

34.0 

29.8 

29.0 



19.33<^) 

74.00 

19.50 

26.87 

21.76 

30.23 

7.26 

7.28 
22.07 
24.19 

9,59^^) 

6.21 
1948.0 
20.66 
53.98 
19,18 
39.00 
24,29 
20,29 



30.4 


18.29 


NA 


6.54 


NA 


D 


NA 


8.46 


NA 


-2.? 8 


NA 


9.62 


30.0 


35.00 


25.0 


50.00 



6-22 



Table 6-7. ACS Voltages and Currents 



Function 




Orbits 




Units 


0/1 


T/V* 
25°C Values 


29 


1081 BMP 1 MTR Volts 


VDC 


36.39 


36.1 


OFF 


1082 RMP 1 MTR Current 


Amps 


0.26 


0.252 


OFF 


1080 RMP 1 Supply Volts 


VDC 


-23.33 


-23.7 


OFF 


1091 RMP 2 MTR Volts 


VDC 


29.82 


30.1 


29.99 


1092 RMP 2 MTR Current 


Amps 


0.10 


0.108 


0,10 


1090 RMP 2 Supply Volts 


VDC 


-23.52 


-23.5 


-23.63 


1220 SAD RT MTR WNDNG Volts 


VDC 


-5.61 


5.7 


-5.47 


1240 SAD LT MTR WNDNG Volts 


VDC 


-5,64 


5.7 


-5.08 


1227 SAD RT -15 VDC Conv. 


VDC 


15,11 


15.6 


15.14 


1247 SAD LT -15 VDC Conv. 


VDC 


15.22 


15.7 


15.23 


1056 CLB + 6 VDC 


TMV 


2.35 


2.32 


2.35 


1055 CTiB + 10 VDC 


TMV 


2.87 


2.87 


2.88 


1057 CLB Power Supply Volts 


TMV 


2.95 


2.95 


2.97 


4006 MMCA Roll Coil 


TMV 


2.99 


3.00** 


2.99 


4005 MMCA Pitch Coil 


TMV 


3.12 


3.20** 


3.15 


4004 MMCA Yaw Coil 


TMV 


3.05 


3.00** 


3.05 



*Thermal Vacuum Test Data 
**20°C T/V Values 



6-23 



Table 6-8. Pre -Launch R/T CRT Hardcopy on the Pad 





PP*t REAL 


TIME SET 


ACS 


»» T " " T 


^-■._-....^.__^. ..__.. 


' 'rw" -y- --WW 




ff» 


IfifviSADECAM 


TIME 10/28/»66tfe TIME 08t/17^«5/19 


RMB 


1 2 


tJ»» 


#^tt«f!Be8S 


7.26 


7»«B 


RSI 


PNEUMATICS 


QYBB T 


79*6^ 75*1 


SO D9C»»* 


#lf*«HBCi T 


afi09 


SiS4 


OQC 


INK P 191tt«3 PSI 


MTB I 


0*2SH 0*1 


lOL AiiP»t» 


"CttOkB V 


19*31 


15f8l 


VOC 


INK T 19t33 D9C 


MT8 V 


36*2SH 89*: 


^3 ?K\t9f 


#^».F 8S T 


15*26 


15it7 


OQC 


MAN P 72»99H PSI 


HTB PWR 


13**2 13*( 


30 WTSflf* 


#»'».R SS T 


16*99 


I9i6» 


OQC 


MAN T 1»»17 DQC 


PKB T 


83*80 30.1 


50 oactf* 


«**>**SB PRE 


3*06 


3f06 


TMV 


CI.B PITCH 


R8CL 


(REAR) YAM 


*P* 


«»M,HT M T 


83*68 


29f88 


OQC 


r/W SPO •S*66 




•11.63 


RPM 9f* 


>»(•*««? W V 


p24i99 


-24t09 


VOC 


CR6 ERR 0>39 


OtSO 




OEQ ##• 


*»C*.TACH 


0*t8H 


•0f89 


0/M 


FNE ERR 0»U 


•Otl6 




oe» ♦•♦ 


ItMtBSANNERS FMD 


REAR 




M»D CW 0*00 


'(tfO 


5f49 0*00 


PCT ft* 


I'f^'tiriN 5P 


627*76 


61B*00 


(tPM 


M*0 CCH 0*00 


0*80 


OfOO 0*00 


PCT ff* 


Pf**9KSi 


9**6H 


6il0 


i8I 


PNC P1S0 


ltt7 


0*00 


TMV #•♦ 


^##.MTR T 


21*37 


29tt6 


OQC 


SBL DC 0*39 


OtSO 


0*00 


PCT M* 


>n»».PRE T 


21*36 


25t56 


OQC 


PITCH nc 0.00 






RPfl ♦#• 


pftSif T 


J7*89 


26tB0 


OQC 


YAW RATE QYR9 


TEMPi-OOC 


CLB VBUTAQES-TMV f** 


«>#*iiifKPLSE 


0*95 


OiOOH 


H$ 


SPESO *n75 TMV 


BPLl 24' 


•87 *-iOV 2i 


•B7M ♦*• 


(»<**. T8PU8e 


0*00H 


IfOO 


148 


RATE 0*00 O/S 


BPLI 83' 


•l* ♦•6V 2i 


>39 ♦•* 




0*70 


0(70 

i«*tttttt*tt 


OEO 


HSQ T 28*39 OQC 


BPL8 S5< 


•99 PS V 2i 


i95H *f« 



Table 6-9. Orbit 1 R/T CRT Display Hardcopy Post Launch 



#**8SAy£CA 
#»*8pPtSS 
#*#8HStJ T 

**#*F bS T 

***8N ys T 

**#8SS P9£ 
*»#»MT ^ T 

#i^#tTAQH 

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PNEUKATICS 
INK P 1923*78 PSI 
TNK T 20*33 DGC 
MAN P b4*3S PSI 
MAN T 18*tS3 DGC 
CLB PITCH 
r/w SPD •122*66 
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RATE 2*0C D/S 
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Table 6*10. Attitude Control System Alignment Data (Prelaunch) 



Control Axes to Spacecraft 


Axes 


Spec 


Measured 


Pitch Axis 




o 
0.25 


-2' 6" 


Roll Axis 




0.25? 


+0' 9" 


Yaw Axis 




0.25° 


-0' 51" 


Pneumatic Nozzles 




Spec 


Measured (Max) 


Pitch 




40' 


4' 


Roll 




40' 


2' 


Yaw 




40' 


7.5' 



Table 6-11. Unfold Subsystem 



Components 

Unfold Timer S/N 6549349 
Unfold Switch S/N 4-32116 
Separation Switches S/N 209 & 211 
Unfold Motors S/N 112 & 113 
Cable Cutter Assembly S/N 55 & 81 

Performance Spec 

Unfold Timer Fire Time 1 2* 7 + 0. 6 Sec 
Unfold Timer Fire Time 2 5* 3 + 1* 2 Sec 
Squib Fire Cxirrent 2 ^4 Amp Ea. 
Squib Fire Current 2 s 4 Amp Ea. 
Paddle Open Time (-Y) ^40 Sec 
(+Y) ^25 Sec 

Pre -Launch Problem Stttnmary 

No Problems Throu^out Environmental Test Program 


Pre-Launch Measurements 


2. 8 Sec 
5.65 Sec 
7 Amp Ea, 
7 Amp Ea. 
25,2 Sec 
16. 2 Sec 



6-25 



Table 6-12. Attitude Control Subsystem 



Parameter 


Spec 


Pre-Launch Measurement 


15 Second Timer 
50 Second Timer 


14. 4 to 18 Sec 

42.5 to 57.5 Sec 


16 Sees 
51 Sees 


Pitch Pneu. Threshold 
Roll Pneu. Threshold 
Yaw Pneu. Threshold 


5.5° + 0.8° 
5,10 + 0.80 
0.07 to 0.13°/Sec 


5.85° 
5. 70 

0. 1030/sec 


Pitch Position Bias 
Yaw Position Bias 


4.7 +0. 50 
1.00 (Trend) 


5.0O 
0. 978° 


Left Solar Array Drive 






Normal Rate 
High Rate 


3. 33 + 0. 33°/Min 
3.90 +0.4O/Min 


3.30°/Min 
3.90O/Min 


Right Solar Array Drive 






Normal Rate 
Hi^ Rate 


3.33 + 0.33°/Min 
3.9 +O.40/Min 


3.45°Alin 
4. 040/Min 


Momentum Bias Speed 


1060 + 150 RPM 


1000 RPM 


Pneumatics 






Primary Seat Leak 
External Leak 


1 SCC/Hr 
10 SCC/Hr 


0. 12 SCC/Hr 
< 0.1 SCC/Hr 



Table 6-13, Attitude Control Subsystem LANDSAT-2 Performance 



Roll 

Pitch 

Yaw 



Spacecraft Goals 



Attitude 

0.7° 
0.7° 
1.0° 



Rate 



0.015 /Sec 
0.015°/Sec 
0. 015°/Sec 



6-26 



SECTION 7 
TELEMETRY SUBSYSTEM 



SECTION 7 
TELEMETRY SUBSYSTEM 

The Narrow Band Telemetry samples, encodes, formats, and transmits data from spacse- 
craft service and payload subsystem to earth receiving stations. The subsystem processes 
and coherently retransmits an S-Band signal, including a ranging code for use in orbit deter- 
mination. The subsystem provides timing and synchronizing signals to spacecraft service 
and payload subsystems. See Figure 7-1 and 7-2 for functional block diagram, and Figure 
7-3 for hardware illustration. The vuiits in this subsystem are closely associated with those 
described in Section 11, Unified S-Band/Premodulation Processor, and Section 8, Command/ 
Clock Subsystem. 

The Telemetry subsystem was launched in the ON mode and has been operating continuously 

providing data from the spacecraft either to ground stations, to the narrow band recorders, 

or to both* The launch configuration is given in Table 7-1 and typical telemetry values in 
Table 7-2. Total performance has been excellent. Prelaunch performance is shown in 

Table 7-3 for the VHF transmitter • 

Table 7-1. Telemetry Subsystem Launch Mode 





MODE 


CMD 




MODE 


CMD 


POWER 1 


ON 


522 


ANALOG MUX 


A 


262 


POWER 2 


ON 


520 


DIGITAL MUS 


A 


300 


MEM WRITE 


OFF 


361 


MEMORY 


A 


240 


VER MEM 


OFF 


422 


FOR LOG 


A 


302 


MTX VER O/R 


ON 


341 


VHF XMTR 


YES 


400 


B.t 1 


OFF 


401 


VHF XMTR O/R 


ON 


342 


B.tO 


OFF 


343 








FOR PROG 


ON 


462 


VHF Tra 


nsmltter 




MTX VER 


NORM 


502 








MEM/VER O/R 


ON 


500 


VHF MODE 


RT 


207 


PRE REG ON 


A 


460 


VHF PB O/R 


ON 


230 


PRE REG OUT 


A 


463 


VHF RF PWR 


LO 


210 


BUFF AMP 


A 


440 


VHF PWR 1 


ON 


206 


SEL SEQ 


A 


242 


VHF PWR 2 


ON 


170 


A/D CONV 


A 


260 


VHF XMTR 


A 


231 



7-1 



4 MHi 1 Hi 



SERiAl 
DIGITAL 
INPUTS 



CONTftOU SIGNALS 
TO SUBSYSTEMS 
h INSTRUMENTS 



COMMAND 

MEMORY 

UNLOAO 




GflOUNO 
COWMANDS & 
ftEPROGnAMMiNG" 
DATA 



SPACECRAFT 

REPROGRAWMJNG 

DATA 



ANALOG 
!*^PUT', FROM 
5U9SYSTEMS 
& rNSTRUMENTS 



BiNAHY INPUTS 
FROM SUBSYSTEMS 
& iNSTRUMEraS 



TO PREMOOULATION 

PHOCESSOR 

IPART OF US& SUaSYSTEM) 



TO 

PREMOOULATION ' 
PROCESSOR 



REALTIME 
TELEMETRY 



PLAYBACK 
TELEMETRY 



(PACMOD FILTERED) 



NARROWBANO 

TAPE 

RECORDER 



NfARROWBAND 

TAPE 

RECORDER 



NARROWBAND TAPE RECOROERS 



COMMANDS 

tNCLUDING FORMAT 

SELECTION 



' PCM OUTPUT 11 Kbpi. SPLIT PHASEl 
11 PCM TELEMETRY 
b> T*ME CODE 

cl COMMAND CLOCK UM.OaO 
di REPROGRAMMING MEMORY READOUT 
tl FORMAT MATRIX READOUT 



V 



A 




TRANSMITTEF 







VMF TRANSMITTER 







TRANSMITTER 










JOQ M'// FOR BEACON OR 
BEACON - REALTIME T/M 



2 WATT FOR BEACON 
PLAYBACK T;M 



'MULTIPLEXING GATES APE ThE 
ONLY NON-REDUNDANT PART OF 
PCM TELEMETRY PROCESSOR 



Figure 7^1. Narrowband Telemetry Block Diagram 



7-2 



582 
ANALOG 

_J_ 



320 
DIGITAL 

_1_ 



16 TEN BIT 
DIGITAL 

_L 



VERSATILE INFORMATION 
PROCESSOR (2) 



n 



KB PS 



t 



WIDEBAND 

TAPE 
EC0RDERI2) 



I 



1KB PS 



NARROWBAND 

TAPE 
RECORDER (2) 



1KB PS 



DZ 



24 KB PS 



1KB PS 



V 




1KB PS 



24 KB PS 



VHF 

TRANSMIHER 
(2) 



137.86 
MHz 

300 MW/2W 
PM 



V 



PREMODULATION PROCESSOR 

(2) 



401 
MHz 



„9V 

^^ L 



t 1024 K 



UNIFIED S-BAND 

TRANSMIHER 

(2) 



2287.5 MHz 
IWAH 



DATA 

COLLECTION 

SYSTEM 



KHZ 

I 
I 
I 



COMPOS ITE/PM 



|_RECEIVER (2)J 



\ 

Cx5 



Figure 7-2. Narrowband Telemetry and Cominand Subsystem Block Diagram (Down Link) 



-4 



So 



e 




NARROWBAND TAPE RtCORDtR 






ilHOSY Jl «tl»ORt $ *?f|»R0G8A»IIER| 




VEftSATRf IHfORJS/iATmH PROCESSOli 



..m^^- 






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INTERFACE SWITCHING MOOUlf 



Figure 7-3. Narrowband Telemetry and Command Subsystem 





*^"f ^msmjuff 



Table 7-2. TMP Telemetry Values 



Function 
No. 


Function Name 


Unit 


Orbit 
O-l 


T/V* 
20° Plateau 


Orbit 
35 


9001 


Memory Sequencer A Converter 


VDC 


4.45 


4.46 


4.45 


9002 


Memoiy Sequencer B Converter 


VDC 


OFF** 


4.55 


OFF*^ 


9003 


Memory Sequencer Temp 


OC 


15.00 


25.00 


20.00 


9004 


Formatter A Converter 


VDC 


4.50 


4.50 


4.52 


9005 


Formatter B Converter 


VDC 


QPJ** 


4.55 


OFF** 


9006 


Dig. Mux A Converter 


VDC 


4.20 


4.22 


4.22 


9007 


Dig. Mux B Converter 


VDC 


OFF** 


4.20 


OFF** 


9008 


Formatter/Dig Mux Temp 


°C 


17.50 


25.00 


25.00 


9009 


Analog Mux A Converter 


VDC 


4.02 


4.02 


4.02 


9010 


Analog Mux B Converter 


VDC 


OFF 


3.87 


** 
OFF 


9011 


A/D Converter A Voltage 


VDC 


4.02 


4.02 


4.02 


9012 


A/D Converter B Voltage 


VDC 


OFF** 


4.07 


OFF** 


9013 


Analog Mux, A/D Conv. Temp 


°C 


17.50 


28.00 


25.00 


9014 


Preregulator A Voltage 


VDC 


3.99 


3.99 


4.00 


9015 


Preregulator B Voltage 


VDC 


OFF** 


4.01 


OFF** 


9016 


Reprogrammer Temp 


°C 


17.50 


22.00 


22.50 


9017 


Memory A Converter 


VDC 


4.45 


4.45 


4.45 


9018 


Memory A Temp 


°C 


12.50 


17.00 


17.50 


9019 


Memory B Converter 


VDC 


OFI** 


4.50 


OFF** 


9020 


Memory B Temp 


^C 


12,50 


17.3 


17.50 


9100 


Reflected Power (Xmtr A) 


dBm 


15.29 


14.7 


18,29 


9101 


Xmtr A-20 VDC 


VDC 


3.97 


3.97 


3.80 


9103 


Xmtr A Temp 


°C 


23.59 


20.5 


27,73 


9105 


Xmtr A Power Output 


dBm 


25.79 


25.7 


27.73 



* Thermal Vacuum Test data 
** Not turned on since Pre launch 



7-5 



Table 7-3. VHF Transmitter 



Component 








VHF Transmitter 


FT 0004 






Pre-Laimch Performance 








1 KBPS real time 
24 KBPS playback 


Data Good 






Spec 
Power Output-Low Mode 300 MV 
High Mode 2 W 


A 
365 MW 

2.8 W 


B 

390 MW 
2. 9 W 



7-6 



SECTION 8 
COMMAND/CLOCK SUBSYSTEM 



SECTION 8 
COMMAND/CLOCK SUBSYSTEM 

The Command and Clock Subsystem consists of the following modules: VHF Receiver; 
Command Integration; Command Clock; and ECAM. The first three modules are located in 
the sensory ring, and ECAM is located Inside the USB antenna mount. Parts of two other 
modules (Unified S-Band Equipment and Premodulation Processor) provide one of the two 
primary inputs to the Command and Clock Subsystem, but are not considered part of the 
subsystem* 

The Command and dock Subsystem performs the following functions: 



1. Receives, processes, and stores command information from the USB and VHF 
ground station. 

2. Receives, processes, and stores command information from the USB and VHF 
ground stations and executes these commands at the predetermined time, 

3. Receives and transfers serial data to the TMP for reprogramming its memory. 

4. Provides an accurate time base upon which all spacecraft activities can be planned, 
referenced, and measured. 

5. Generates Minitrack 36-bit time code data which is stored and transmitted with 
TMP, RBV, and MSS data so that the time reference cited above may be used to 
process data in the ground station, 

6. Generates standard frequencies and motor drive signals used by other subsystems. 



The LANDSAT-2 System Command Matrix provides for 512 commands as noted in Appendix 
B. 

Figure 8-1 is a simplified block diagram and Figure 8-2 is a modulation format. 

The LAKDSAT-2 command subsystem was launched in the configuration given in Table 8-1, 
and activated with the separation and unfold contact closure which occrrred at, 18:54:55 
near Tananarive in orbit 0. 

8-1 



00 

\ 
to 



V 



MOTCH 
FILTER 



VHF RECEIVER 



DC/OC 
COrJV 



I5VDC 

10 VDC 



J YA J 



RF 


1 
1 








SPLITTER 




(SI 
















RFJF 


OEMOD 











xe i 

VB } 



-IS voc 
10 voc 



1 TT 



V 



U5S RCVR 



REDUMDAKITSU BMODU LE5 
NOT PART OF CAC S.S 






COMMAND INTEGRATOR UNIT 



OC-OC 
CONV 



^4^ 



TTTT 



SUEJ-BJT 
DECODER 



DECOoe' 
PVR 



4 5 A 



IJC^OC 
CONV 



TT 



i i i 



sua SIT 

DECODER 



CMD 
DECODE' 



1 T 



^ AMCBO 
AMC6< 



PWR - 
ISM ef?D - 



,^BMCAO 
^BMCAl 
*'BMCBO 



DISCRETE CMD 
CLK 

PWR 



n 



COMMANp 9^,9tfS 



-{ 



STORED CMOS " 



DCVDC 
CONV 



^^^ +5 VI 



VDC 
;3 VDC 
£9 VDC 



DO'DC 
COHV 



STORED CMOS 



I 



MIX. 
DECODER 



■4]' 



4^' 



<?1 



®- 



FRED 
GEN 



-^- TIME c€oe 



i-STDFRBQ 



^ MTB DRtVES 



MB 
DVBS 



Figure 8-1. Command and Clock Subsystem Block Diagram 



oo 

^ hi 

^63 



ZERO ONE ZERO ZERO ONE 

r r 1 n^^ 




SYNC SIGNAL CROSSOVER POINT SHOWN HERE AT 
THE 1/2 BIT PERIOD INTERVAL 



INCIDENTAL AM AT BIT EDGES 



J 



< 20% OF ENVELOPE 
COMPOSITE 



AUDIO SIGNAL 



SCO FREQUENCY » ±0.1% 






MAX CROSSOVER 
ERROR (B:;T SYNC) 

5% ' 



2; 
H o 









u. 



O 



50 ± 5% g 2 

S 9 



T 



BIT SYNC 
MODULATION 



DISTORTION < 10% 
FREQUENCY ±0.1% 



DIGITAL 



5% 



MODULATION 
PCM - NRZ 



00 



Figure 8-2. Composite STADAN Audio Waveform 



Table 8-1, Command/ Clock Subsystem Launch Mode 





Mode 


Cmd 


COMSTOR A 


OFF 


055 


COMSTOR B 


OFF 


025 


MTX DECODER 


PRl 


Oil 


MTX A DRIVE 


PR! 


012 


MTX B DRIVE 


PRl 


013 


OSCILLATOR 


PRl 


014 


FREQ. GEN 


PRl 


015 


VERIFY 


TOCK 


457 


MSFN/STADAN 


A/B 


616 


CLOCK FUSE 


lA 


653 


CIU CH B 


ON 


782 


cru CH A 


ON 


786 


CLOCK PS/COM 


ON 


783 


ECAM 


OFF 





A summary of telemetry values Is provided in Table 8-2. Flight data correlates very closely 
■with Thermal Vacuum test data values. Ground software problems are delaying availability 
of some of the telemetry. 

Command processing of both real time and stored commands have been normal. No spurious 
or unexecuted commands have been observed. (Some commanding difficulties have been 
experienced, but all eases have been coincidental with low elevation at the station, lock on 
side lobes, or similar ground transmission difficulties. ) 

The time base provided for spacecraft activities planning has been well within specifications 
during this period. Clock drift has been less than -2 MS per orbit during this period. 

Spacecraft time code, transmitted via REV, MSS, and Tim has been reliable and accurate. 

All frequency outputs to other subsystems have been nominal. 

Table 8-3 shows the pre-launch performance of the Command Clock subsystem. 



8-4 



Table 8-2. Command/ Clock Telemetry Summary 



Function 








Orbit 


Thermal Vac 


Orbit 


No. 


Name 


Mode 


Units 


0/1 


20^ Plateau 


35 


8005 


Pri, Power Supply Temp. 


- 


"c 


29.93 


37.89 


38. 82 


8006 


Red, Power Supply Temp, 


- 


**c 


27.61 


36.31 


36.93 


8007 


Prl. Obc, Temp. 


- 


^c 


24.35 


27,84 


28.70 


eooe 


Red Osc. Temp. 


- 


"c 


23.48 


26.95 


27.82 


8009 


Prl. Oec. Output 


- 


TMV 


1,02 


1.06 


1.06 


6010 


Red, OflC. Output 


- 


TMV 


0,0 


1.16 


3.20 


80U 


100 KHz 


Prl. - Red. 


TMV 


3.15 


3,16 


3.17 


8012 


10 KHz 


Prl. - Red. 


TMV 


3.04 


3.05 


3.08 


8013 


2. 5 KHz 


Prl. - Red. 


TMV 


2.95 


2.96 


3.01 


8014 


400 Hz 


Prl. - Red. 


TMV 


4.43 


4.45 


4.17 


8015 


Pri, / 4V Power Supply 


Prl, ClkON 


VDC 


NA 


2.05 


NA 


8016 


Red, / 4V Power Supply 


Red. ClkON 


VDC 


NA 


2.01 


NA 


8017 


Pri. / 6V Power Supply 


Pri, Clk ON 


VDC 


NA 


2.31 


NA 


8018 


Red, 7^ 6V Power Supply 


Red, ClkON 


VDC 


NA 


2.31 


NA 


8019 


Pri. - 6V Power Supply 


Pri, Clk ON 


VDC 


NA 


5.23 


NA 


8020 


Red, - 6V Power Supply 


Red. ClkON 


VDC 


NA 


5.23 


NA 


8021 


Prl. - 23V Power Supply 


Pri, Clk ON 


VDC 


NA 


5,70 


NA 


8022 


Red, - 23V Power Supply 


Red. ClkON 


VDC 


NA 


5.66 


NA 


8023 


Pri. - 29V Power Supply 


Pri, Clk ON 


VDC 


NA 


5,29 


NA 


6024 


Red. - 29V Power Supply 


Red. Clk ON 


VDC 


NA 


5.28 


NA 


6101 


Cro A - 12V 


cm A ON 


VDC 


3.96 


3.96 


3.79 


6103 


CrU B - 12V 


cm B ON 


VDC 


3.95 


3.95 


3.78 


8103 


CrU A - 5V 


cm A ON 


VDC 


4.14 


4.15 


3.93 


6104 


cm B - 5V 


CIU B ON 


VDC 


4.10 


4.10 


3.90 


8105 


cm A Temp. 


cm A ON 


"c 


20.69 


22.52 


26.01 


8106 


cm B Temp. 


CmB ON 


^c 


18.98 


20.52 


23.35 


6201 


Reoelver HF-A Temp. 


- 


"c 


NA 


30.05 


NA 


8202 


Heoelver RF-B Temp, 


" 


°c 


28.18 


26.08 


23,09 


8203 


D MOD A Temp. 


- 


"c 


26.05 


39.03 


28,95 


8204 


D MOD B Temp. 


- 


*^c 


35.68 


29,16 


37.73 


8205 


Receiver A AGO 


Receiver A ON 


DBM 


OFF** 


-56. 94 


OFF** 


6206 


Receiver B AGO 


Receiver B ON 


DBM 


-85. 72 


-61. 46 


-87. 83 


6207 


Amp. A Output 


Receiver A ON 


TMV 


OFF** 


1.49 


OFF** 


8202 


Amp. B Output 


Receiver B ON 


TMV 


1.76 


1.55 


2.10 


6209 


Freq. Shift Key A Out 


Receiver A ON 


TMV 


OFF** 


1.08 


OFF** 


8210 


Freq. Shift Key B Out 


Receiver B ON 


TMV 


1.10 


1.11 


1.11 


6211 


Amp. A Output 


Receiver A ON 


TMV 


OFF** 


1.11 


OFI^* 


8212 


Amp, B Output 


Receiver B ON 


TMV 


1.13 


1,13 


1.13 


8216 


D MOD A - 15V 


Receiver A ON 


TMV 


OFF** 


4,87 


OFF** 


8216 


D MOD B - 15V 


Receiver B ON 


TMV 


4.77 


4.78 


4,77 


8217 


Regulator A - lOV 


Receiver A ON 


TMV 


OFF** 


5.40 


OFF*+ 


8218 


Regulator B - lOV 


Receiver B ON 


TMV 


5.30 


5.33 


5,32 



* 'nitrmal Vacuoin Teat Data 
** A component not uaed alnce Pre-laumch 
NA - not available due to procesalng 
problem - MTT 710 



-^OOR QUALITY 



8-5 



Table 8-3. Command and Clock Subsystem Pre-Launch Performanoe Summary 






ALL OPERATIONAL MODES EXERCISED SATISFACTORILY 

BOTH COMSTORS OPERATED. ALL STORED COMMANDS EXECUTED PROPERLY 

ALL cm COMMANDS EXECUTED PROPERLY 

NO TIME CODE OR CLOCK FREQUENCY ANOMALIES 

ALL SERIAL DATA COMMANDS TO ECAM OPERATED PROPERLY 

ALL ECAM STORED COMMAND LOCATIONS (512) EXERCISED. ALL ECAM 
STORED COMMANDS EXECUTED PROPERLY. 

ALL ECAM SMART FUNCTIONS EXERCISED AND FUNCTIONED PROPERLY. 
VHF RCVR THRESHOLD 

SPEC ^ ^ MARGIN 

-107 DBM -108 DBM -107 DBM 31. 6 DB 



PROBLEM 

cru 

• NONE 
VHFR 

• AG C VARIES WITH TEMPERATURE. 
TRACKING SINCE LAST REVIEW. 



ECAM 

• STOPS PROCESSING DATA WHEN 
REDUNDANT SYSTEM SWITCHED IN 
(EBPR268, 5/29/74). 

• SMART FUNCTIONS EXECUTED WHEN 
VIP RECONFIGURED (EBPR 309, 

6/1/74). 



RESOLUTION 



• NO PROBLEM - RE PEAT ABLE AT ANY GIVEN 
TEMPERATURE. HAS NOT CHANGED, DOES 
NOT AFFECT SPACECRAFT OPERATION. 
ACCEPT AS IS. 



• INTERRUPTS CAUSED BY RE- CONFIGURATION 
OF COMMAND CLOCK AND/OR VIP. 
RESTRAINT ADDED, 

• INADEQUATE SYNC CRITERIA. CRITERIA 
MADE TIGHTER - PROBLEM RESOLVED. 
SOFTWARE MODIFIED TO SOLVE PROBLEM, 



COMMAND CLOCK 

• POWER SUPPLY INSTABILITY AT HIGH • 
TEMPERATURE (P/S TEMP 50°C) AND 
LIGHTLY LOADED, (EBPR 27^, 
5/29/74 MRD08198). 

• EXECUTED ^»COMP LOAD #2 ON'^ • 

COMMAND WHEN THE REDUNDANT 
CLOCK P/S WAS TURNED ON, 
EBPR (530, 10/25/74). 



UNIT REMOVED FROM SPACECRAFT AND 
RETURNED TO CAL COMP FOR REPAIR, 
(PRIOR TO T/V #2). 



PROBABLY CAUSED BY NOISE AT P/S 
TURN-ON. HAS NEVER REPEATED, 
CLOCK P/S TURN ON IS NOT A NORMAL 
OPERATIONAL EVENT (BOTH SUPPLIES 
ON AT LAUNCH AND REMAIN ON). 



8-6 



SECTION 9 
ORBIT ADJUST SUBSYSTEM (OAS) 



SECTION 9 
ORBIT ADJUST SUBSYSTEM (OAS) 

The Orbit Adjust Subsystem (OAS) is a monopropellant hydrazine fueled propulsion system 

consisting of three thjruster assemblies, a propellant feed system, a support structure and 

the necessary interconnect plumbing, brackets, and electrical harnessing. The propellant 

feed system consists of a single tank for storage of both the propellant and pressurant. The 

feed system operates in a blow-down mode during which the engine thrust decays from an 

initial level of 0, 85 LB^ to a final value of 0, 25 LB„ as the 67 LB of propellant is constnned, 

I I m 

The operation of the propulsion subsystem permits the flow of hydrazine propellant into a 
combustion chamber containing a catalyst. Within the chamber, the catalyst spontaneously 
decomposes the hydrazine into ammonia, hydrogen, and nitrogen gases having a temperature 
of approximately 1800 F» These gases are then expanded through a conical nozzle to pro- 
duce thrust. See Figures 9-1 and 9-2 for functional block diagrams and Figure 9-3 for hard- 
ware configuration. 

The OAS was launched in the OFF mode and remained OFF except as noted in Table 9-1, 



Table 9-1. 



Orbit 


Burn Time 
(Sec) 


Semi Major 
Axis** (KM) 


Performance 
% of Plan 


N2H4 
Used (LBn,) 


_* 


- 


7286.462 


- 


- 


32 


4.8 


7286. 501 


105.41 


0.02 


71 


4.8 


7286.434 


90.00 


0.02 


79 


420 


7289.977 


107. 07 


1.62 


86 


420 


7293.191 


107. 02 


1.51 


163 


420 


7290.237 


97.00 


1.42 


191 


360 


7287. 816 


97.58 


1.15 


212 


308.8 


7285.820 


101. 52 


0.95 


Average F( 


)ree w 0.79 LBj 









*After Injection 
**Post Burn 



9-1 



In Orbit 32 a 4. 8 sec burn was performed to test the alignment of the -X thruster. A sim- 
ilar firing was performed later in Orbit 71 on the +X thruster* In both cases the firing was 
normal. Jn Orbit 79 an orbit adjust sequence for LANDSAT-2 was initiated to phase the sat- 
ellite with LANDSAT-1 in the 18 day ground track repeat cycle. A firing on the -X thruster 
in this orbit lasted for 420 seconds, and was normal in all respects. In Orbit 86 the -X 
thruster was again fired for a duration of 420 sec, which brought the semi-major axis of 
the orbit to 7293. 19 km. Later, in Orbits 163 and 191, the -fX thruster was fired for a 
duration of 420 and 360 seconds respectively. The final maneuver in this sequence was per- 
formed with a firing on the +X thruster in Orbit 212, The burn lasted for 308. 8 seconds. 
Tracking data has confirmed satisfactory achievement of all objectives of this orbit adjust 
sequence. A summary of the orbit adjust maneuvers is given in Table 9-1, The typical 
performance characteristics of the +X and -X thruster s are shown in Figures 9-4 thm 9^7. 

Housekeeping fimctions of the OAS were normal. Table 9-2 gives average telemetry values 
for the OFF quiescent state. 





Table 9-2. 


OAS Telemetry Values 








Function 


Units 




Average Values 




No, 


Name 


Orbit 
0-1 


20°C Plateau* 


Orbit 
50 


2001 


Prop. Tank Temp. 


"c 


18.35 


19.0 


23.03 


2003 


Thrust Chamber No. 1 (-x) 
Temp 


°c 


25.38 


19.7 


24.84 


2004 


Thrust Chamber No. 2 (+x) 
Temp 


^c 


20.47 


18.3 


37.34 


2005 


Thrust Chamber No, 3 (^y) 
Temp 


"c 


40.33 


18.0 


47.22 


2006 


line Pressure 


Psia 


531.71 


15. 0** 


545.60 



♦Thermal Vacuum Test Data. The Thruster Chamber heaters were duty cycled to maintain the 
chamber temperatures between +5°C and 440*^C. 

*^* (Orbit Adjust Tank not Loaded) 



9-2 



PRESSURANT 
FILL VALVE 

SEPARATION 
DIAPHRAGM 




TANK 



PROPELLAMT TANK TEMPERATURE 
{TLM 200 



PROPELLANT 
FILL VALVE 



m 



SOLENOID 1 ON/OFF 
(CMD 670/745) 

SOLENOID VALVE NO. 1 ON/OFF 
(TLM 2007) 



S FILTER 



s 



h -X AXIS THRUST CHAMBER NO. 1 
TEMPERATURE (TLM 2003) 



SOLENOID 2 ON/OFF 
(CMD 711/745) 

SOLENOID VALVE NO. 2 ON/OFF 
ITLM 2008) 



LINE PRESSURE 
(TLM 2006) 



A 



+X AXIS THRUST CHAMBER NO. 
TEMPERATURE (TLM 2004) 



SOLENOID 3 ON/OFF 
(CMD 732/745) 

SOLENOID VALVE NO. 3 ON/OFF 
*TLM 2009) 



ORBIT ADJUST THRUSTER HEATER 
rm ON/OFF (CMD 615/657) 

3-Y AX*S THRUST CHAMBER NO. 3 
TEMPERATURE (TLM 2005) 



CD 

I 



Figure 9-1. Orbit Adjust Subsystem Block Diagram 



CD 

I 






THRUSTER UTILIZATION 

#1 - ALTITUDE CORRECTION 
#2 - ALTITUDE CORRECTION 
#3 - INCLINATION CORRECTION 



-^l^^'-^- 






y 



/^k 



ANGLE IN X-Y PLANE 

ANGLE IN X-Z OR Y-Z PLANES 



.<^'' 
^^l,^ 




Figure 9-2, Orbit Adjust Thruster Orientation 




CD 
1 
CJl 



Figure 9-3. Orbit Adjust Subsystem 



mBii n inP iHnBniiiinniiiiiiniiiiniii'iMniiiniiiniMwiiiwi^ 
iiiiiiiiiiiBniiiiiiiiriinBlHllH^^^^ 



BSisSss;^^^^ 



niHiiiHiuiuHiniiiDiitDiuiiiiuiniiiiiDtniiiffiiiiuiinuiiiiiNnin^ 



DlQlillt^lfflllllllluuliillliiiiiinDiniiniiinininniiiiniira 




PROPEL -TANK TEMP 



Ct£R6 
1/16 



THRUST CHAMB TEMP 
CHAMBERS 1St£&3 

1/ie ALL 
F2003/FZOT4/F2005 



.INE PRESSURE ROLL SOi. DUTY CYCLE PITCH SOL DUTY CYC 



creR70 

1/16 
F2D06 



C1DR73 

1/16 

FI032 



C2R73-' 

1/16 

F1045 



YAW SOL 
DUTY CYCLE 

CI8R36 

1/16 

F1037 



<Va acq 

node status 

CZRe 
t/IS 
F1046 



MANIFO-D 

TEMPERATURE 



C1ZR53 
(/1 6 

Fian 



PITCH FW SPEED 

ROLL'WFF TACH PITCH FINE ERROR 



ROLL FWD FW SPEED ROLL FIN! 
ACS CLOCK A 



C5RZ 
F1043 
1/1 



CBRe4 
F103t 
1/16 



F1(M1 
1/1 



C6R0 CiaR7Z 

F1026 F1053 

1/T t/!6 



C5R1 
F103I 
1/1 



FOLDOUT FRAWE 



/ 



ERROR ROLL REAR FW SPEED RMP #1 IND RATE HI RMP#2 IND RATE HI YAW TACH OOTPUT 
ACS CLOCK B 1^ RMP STATUS 



CTROf CERB 

F1027 FrD54 
1/1 1/16 



CdR) 

Fioe7 

t/1 



C7R2 


C6RT 


C11H39 


F1097 


riD35 


F1049 


1/1 


1/' 


1/16 



Figure 9^* Performance Characteristics 



a. 




C17R2 
F20(I7 



PROPeU TANK TCMP THRUST CHAMB T^MF* Lll« PftESSUFffi RCLL SOL DUTY CYCLE PITCH SOL DUTY CYC 
CHAMBERS lBi2&3 



ciene 

FZ001 



CBMVClORSVciiRfll 
. l/IS ALL 

FaooVFaooVFZKw 



CT8fi70 
F2006 



CiaR73 

1/1* 

F1032 



C2R73 

1/16 

F1045 



YAW SOL 
OUTV CYCLE 

eta Rao 

(/I6 
FID3? 



q/A ACQ 

MODE STATUS 



C2R« 

i/te 



MANIFOLD 

TEMPERATURE 



CIZR33 

t/16 
FI211 



ROLL FWD FW SPEED I lOLL HUE 
ACS CLOCK A 



C5R2 CAR64 

F1M3 FlOai 

1/1 f/ia 



C4R£ 
Fr04l 
!/• 



CBBD ctaR7i 

F1026 F1053 

1/1 1/t* 



FOLDOOT nWOOlE 



/ 



'*^r^'^^^»®^^° ""'* *' '"^ ""^ "' ""P ** '"° R^TE HI YAW TACM OUTT»UT 



CER1 
FIPW 
1/1 



ACS CLOCK B 

C7RD C1R0 

T1027 FtDB< 
1/1 1/16 



C9RI 
1/1 



C7na 

now 
1/' 



cmi ciifl35 

F103S FT<M» 

1/1 I/IB 



Figure 9-5. Performance Characteristics 






9-9/10 




OFF ON 
5CI-#1 

CITRa 

raoa7 



OFF ON 

SOLtZ 
C17R3 

F2ao& 



OFF ON 

SOLtl 
CieR4 

FZ009 



IN OUT 

RLKA-YAW 

CIDRI 

Ftoeo 



PROPEL TANK TCMP THRUST CHAMB TEMP LINE PftESSURE ROU. SOL DIXTY CYCUE PITCH SOL DUTY CYC 
CHAMBERS 1&Z&3 



ciaRS 

1/16 
FJ001 



CaR4VClOR5VCI2R6l 

l/lfi ALL. 
FZOOVFZOOVF^OOS 



CfBR7D 
1/16 

F200e 



C10H73 

1/16 

F103a 



CZR73 
1/16 

F1049 



YAWSOL 
Oin^ CYCLE 

CteR36 

T/lfi 

n037 



q/AAOO 
MODE STAT\IS 

C2Ri 
1/16 
F104e 



MAHIFOI.D 

TEMPERATURE 



CIZR53 

t/16 

FIZ11 



PITCH FW SPEED 

ROLL DIFF TACH PITCH FINE ERROfT 



ROLL FWD FW SPEED ROLL FINE 
ACS CLOCK A 



C5R2 C0R64 

FI(M3 F1031 

1/1 1/16 



^RRO« ^<^^^^^^^P^^^ RMP , , ,^:j ratK hi RMP #2 IND RATE HI YAW TACH OUTPUT 

P/Y RMP STATUS 



C4R£ 
FI041 

1/1 



C6R0 

F1026 
1/1 



CIBRTZ 
FfOS3 

1/16 



CSRf 

F(03O 
t/1 



FOLOOlJr FRAME 



/ 



C7R0 C1R8 

FT0Z7 Ft034 
1/J 1/16 



CBRI 


CTRi 


CBRt 


FIOBT 


F1«7 


F1035 


1/1 


1/1 


1/t 



C12R35 

FI0« 

f/ta 



Figure 9-6. Performance Characteristics 



HOLDOUT FRAME 

6-- 



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1 






\f 


F 


.OFF ON 
'S0L#1 

C17R2 

FZ0O7 

'ROPEL TAN K TEMP THRUST CHAk 
CHAMBERS 1 a 

^■OLDOUT Ri 

/ 


< 

F 

4B 

^C1 

■zw 


OFF 

JOL# 

;i7r: 

-2008 

TEMI 
3 

ZR61 


2 
t 

s 


W OFF 
SOU* 

cieR 

F200E 

LlhE PRESSURE F 

CT8R70 
F2006 


ON IN 
3 RLNA 
1 C10R1 
F1060 

iOLL SOL DUTY CYCLE 

C1CR73 
1/16 

F103Z 


DUT DtS 
-YAW 0// 

CIS 
F2D 

PITCH SOL DUTY 

C2R73 
1/16 

F1045 

ORIGINA 
OF P005 


R3 
35 

CV 

L 

I 


ENA 
IMER 

YAWS 
C DUTYC 

CIBR 

Vie 

F103 

PAGE 
QUALr 


DtS 
O/i 
C1« 

r2( 
ycLE 

36 

7 

IB 

n 


EKA OFF ON 
\ SOL PWR O/A THRUST KTR 
iR4 CIR3 
^jT) F2020 

CyA ACQ MANIFOLD 
MODE STATUS TEMPERATURE 

FTM6 p^2U 






OFF ON OFF ON OFF ON ' OFF ON "US EKA [)|s ENA: i 2 

PITCH SOL PITCH SOL ROLL SOL f,cLL SOL "^^S)^" ""^ "^^ ^^ ^'^ 
C17R3 CieR3 C17R2 Ct6R2 C1R£ CISRI ciSRt 
F106S F1064 F1063 F1062 FlOOS FlOt? fiIJi 

PITCH FW SPEED 

ROLL' m FF TACH FITCH FINE ERROR ROLL FWD FW SPEED ROLL FI NE ERROR f OLL REAR FW SPEED RMP #1 IND RATE HI RMP #2 IND RATE HI YAW TACH OUTPUT 

ACS CLOCK A ACS CLOCK 5 p/y R„p STATUS 

C5R2 CBR64 C4R2 C6R0 C18R72 CSR1 c 7RD CIRB C9R1 C7R2 CSBI cts»« 

Figure 9-7. Performance Characteristics 

Original page is ,--,. tv.. .-,. ^ , o /, . 

OF POOR QUALITY ' '"^"^ ™WE 9"13/14 



SECTION 10 

MAGJMETIC MOMENT COMPENSATING 

ASSEMBLY (MMCA) 



SECTION 10 
MAGNETIC MOMENT COMPENSATING 
ASSEMBLY (MMCA) 

The purpose of the MMCA is to provide means for generating magnetic dipole moments suf- 
ficient to cancel those residual dipole moments that may exist on the spacecraft. The MMCA 
consists of three mutually perpendicular, chargeable, permanent magnetic rods. Activation 
of the charging and discharging mechanism is by commands. See Figure 10-1 for functional 
block diagram. 

The MMCA was launched in the OFF mode as noted in Table 10-1. 



9 DIGITAL "B" 

RELAY 

HOUSEKEEPING 



3 ANALOG 
FLUX DENSITY 



-L^ 



P- 
Y- 



2 ANALOG 

CARD TEMP 



iAl » 

|A2 ^ 



TELEMETRY 

PROCESSING 



TLM OUTPUT 
TO 
TMP 



PITCH 
KS^MAGNET 




YAW 
MAGNET 



ROLL 
MAGNET 



Figure 10-1. MMCA Fiuictional Block Diagram 



10-1 



Table 10-1. MMCA Launch Mode 



POWER 


MODE 


CMD 


OFF 


765 


CAPACITOR 


HI 


744 


CAPACITOR 


DUMP 


706 


POLARITY 


+ 


742 


PnCH COIL 


OUT 


702 


ROLL COIL 


OUT 


761 


YAW COIL 


OUT 


704 



Housekeeping functions of the MMCA were normal. The unit was not activated; insertion of 
dipole values was deferred pending evaluation of the ACS performance. Gating during orbits 
in this period has averaged 0. 8 gates in the +R, 0. 1 gates in the -R, and 0. 5 gates in the +P 
direction per orbit. Table 10-2 gives average telemetry values. 





Table 10-2. 


MMCA Telemetry Values 




Number 


Name 


Units 


Orbit 
0-1 


T/V 


Orbit 
50 


20°C Plateau* 


4001 


Al Board Temp 


°C 


21.54 


21.3 


20.56 


4002 


A2 Board Temp 


°C 


** 


20.6 


** 


4003 


Hall Current 


TMV 


3.40 


3.40 


3.40 


4004 


Yaw Flux Density 


TMV 


3.05 


3.00 


3.05 


4005 


Pitch Fhix Density 


TMV 


3.12 


3.20 


3.15 


4006 


Roll Flux Density 


TMV 


2.99 


3.00 


2.99 



* Thermal Vacuum Test Data 
**Defective Telemetry Function 



10-2 



SECTION 11 

UNIFIED S-BAND/PREMODULATBDN 

PROCESSOR (USB/PMP) 



SECTION 11 
UNIFIED S-BAND/PREMODU LATION 
PROCESSOR (USB/PMP) 

The Unified S-Band Equipment (USBE) consists of two S-Band transmitter /reiceiver pairs 
(transponders). Each transmitter/receiver pair normally operates as a separate unit. Only 
one of the two is powered at any given time, but it is possible to cross -strap them by ground 
command. When cross- strapped, the receiver of one transponder and the transmitter of 
the other are powered. The USB Receiver receives the uplmk RE signal, demodulates the 
command and ranging subcarriers, and, when possible, provides a phase-locfced oscillator 
signal for the down-link USB transmitter. A ranging (psuedo-random noise-PRN) signal 
is demodulated and is available for modulation of the downlink upon ground command. The 
subcarrier containing command information is sent to the PMP. One of the USB receivers 
is powered at all times. The USB transmitter uses either the phase-locked oscillator of the 
USB receiver or, if sufficient signal for phase -lock is not present, an auxiliary oscillator 
for the transmitter RE driver. Back-up modes allow and sometimes require use of the aux- 
iliary oscillator or the receiver oscillator (phase-locked or free-running) at all times. Mod- 
ulation of the USB transmitter comes from the PMP, and may or may not have the PRN 
ranging signal added. Switching permits either transmitter to be ON or OFF, but both 
transmitters ON simultaneously is not possible. Protection against inadvertent leaving ON 
of either transmitter (and/or either of the wide band power amplifiers) is provided by a 32 
minute cutoff timer. See Figure 11-1 for Functional Block diagram. Figures 11-2 and 11-3 
axe modulation formats. 

The USBE was launched in the OFF mode, as noted in Table 11-1, and activated after sep- 
aration in Orbit near Tananarive. Commands were successfully uplinked in orbit 1 at Mad- 
rid and have continued to be normal since that time. Table 11-2 gives average telemetry 
values. Table 11-3 gives prelaimch measured data. 

At launch, the operational mode was MSFN A/STADAN B, which employs USB-A section for 
both receiver and transmitter. In orbit 45, the operational mode was changed to MSFN 



11-1 



B/STADAN A at 23:08:13 on 25 January. This mode employs the B section of the USB. 
A comparison of the two telemetry readings can be seen in Table 11-2. 

Table 11-1. USB/PMP Launch Mode 



USB XMTR PWR 


Mode 


CMD 


EN 


347 


USE XMTR 


DIS 


757 


AUXOSC 


EN 


150 


SEL XMTR 


A 


126 


RANGING 


OFF 


146 


MOD INPUT 


NORM 


147 





Table 11-2. USB/PMP Telemetry Values 














T/V* 














Average 




FUUCtiOTl 

No. 


Functiou Name 


Mode 


Units 


Orbit 

15 


Value 

20^ 

Plateau 


Orbit 
50 


11001 


USB Receiver AGC 


Receiver A Low 


DBM 


-112.72 


NA 


-120.24 


11002 


USB Transmitter Power 


Transmitter A ON 


WTS 


1.36 


1.40 


1.36 


11003 


Receiver Error 


Receiver A Normal 


KHz 


-2.15 


NA 


-4.87 


11004 


USB Transponder Temp, 


Transponder ON 


°C 


25,88 


22.33 


29,12 


11005 


USB Transponder Pres. 


Transponder ON 


PSI 


17.08 


16.99 


17,00 


11007 


USB Tranflmitter A- 15V 


Transmitter A ON 


VDC 


2.36 


2,35 


OFF 


11008 


USB Transmitter B-15V 


Transmitter B ON 


VDC 


OFF 


2,39 


2.40 


11009 


USB Ranging Mode- 15- V 


Ranging ON Disc. A ON 


vix: 


2.07 


2.07 


2.05 


11101 


PMP A Voltage 


Discrim. AON 


VDC 


-15. 10 


-15.22 


OFF 


11102 


PMP B Voltage 


Ettscrim. BON 


VDC 


OFF 


-15.07 


-14.96 


11103 


PMP A Temp. 


TLM Power ON 


^C 


37.30 


NA 


32.37 


11104 


PMP B Temp. 


TLM Power ON 


OC 


28.34 


NA 


35.16 



Table 11-3. Unified S-Band Subsystem 



Components 

USHE 
PMP 



EAB-QM 
EAB-FT2 



Pre- Launch Performance 



XMTR RF power output 
ncvn CMD t hreehold 
Range delay variation 



Spec 



IW 

-95 DBM 

40 NSEC P-P 



Measured 



1.20W 

-105 DBM 

10. 9 NSEC P-P 



1,18W 
-100 DBM 

5.7 NSEC P-P 



Pre-Launch Problem SUmmary 

No problems throughout environmental test program 



11-2 




CO 



Figure 11-1. USBE/PMP Functional Block Diagram 



1 



fo -495.833 KHz 

fo -70 KHz 



COMMAND SUBCARRIER 

RANGE CLOCK 
PLAYBACK TM 
REAL TIME TM 
DCS 

RANGE PRN CODE 




-„ Upli 

£ = 2287.5 Down Link 
o 



Figure H-2. S-Band Transmission Spectrum 



CLOCK 
1 KHZ 



SUB-BITS 

2 KHZ 
PSK 



V\jW\A/\Aj 



BIT 



tjo[o|i|o[i|o|o 

SUB-BIT CODE 



CLOCK 
1 KHZ " 



SUB-BIT 

PSK WAVEFORM 



FREQUENCY 
MODULATOR 



*E 



70 KHZ 



PSK 



PRN 
(IF ANY) 



2106.4 MHZ 



SUe-BITS 0, 1 



2 KHZ TONE 




USB UPLINK 

SIGNAL 



MSFN COMMAND WAVEFORMS GENERATION 
COMMAND SUBCARRJER ^^ ^ ^^ COHERENT CARRIER 



RANGE 

CLOCK (495, 933 KHZ) 



RANGE PRN CODE 



fo -991.666 KHZ 




fo +991.666 KHZ 



fo -70 KHZ 



fo +70KHZ 



fo = 2106.4 MHZ 



ORIGINAL PAri Figure 11-3, MSFNAJSB Uplink Modulation 



11-5/6 



SECTION 12 
SEPARATION AND UNFOLD SUBSYSTEM 



SECTION 12 
SEPARATION AND UNFOLD SUBSYSTEM 

The Separation and Unfold Subsystem consists of the following components: Unfold Timer, 
Unfold Switch, Separation Switches, Unfold Motors, and Cable Cutter Assembly. At pro- 
grammed separation time, the launch vehicle provides power to fire four electro-explosive 
bolt cutters to effect spacecraft separation. See Figures 12-1 and 12-2 for mechanical ar- 
rangement, and Figure 12-3 for Functional Block Diagram. 

The separation subsystem performed as expected. The 2. 5 second timer caused paddle un- 
fold. Before separation the subsystem properly restrained the paddles, disabled the pri- 
mary and redundant matrix A drivers, provided -24. 5 VDC to the attitude control reset 
line, and provided telemetry signals indicating that the spacecraft was still mated to the 
Delta Vehicle. After separation all circuits were activated and separation was confirmed by 
referring to the strip chart ACS telemetry functions listed below: 

Delta Activation Time From 



Function No. 


Title 


Separation (A Seconds) 


1240 


SAD left MTR WNDG voltage 


52.5 


1220 


SAD right MTR WNDG voltage 


52.5 


1027 


Roll rear flywheel speed 


17.5 


1035 


Yaw tach output 


17. 5 ., 


1040 


Pitch coarse error 


17.5 


1043 


Pitch flywheel speed 


17.5 



All of these fimctions have known activation delta times from separation, and all are read 
each second in the telemetry matrix* 

By measuring the delta times backwards, i. e, , from activation to separation, all of the 
fimctions indeed commence from the same baseline in time, and hence confirm the separation 
time. 

It was necessary to employ this technique because the separation switch fimctions normally used 

to monitor separation were removed from the software programs. 

12-1 



to 

I 

to 




0\A. 



SHROUD 



NOTE: STATIONS CITED ARE SPACECRAFT 
STATION DESIGNATIONS 



Figure 12-1, ERTS Observatory/Shroud Envelope and Minimum Clearances 



TOP 



HINGE 



D 




LEFT 
PADDLE 




RIGHT 

PADDLE 



LATCH CABLE 
(PIN INSIDE JAW 
AT SECTION AA) 



HINGE 



"lE !] 



STOP PLATE 



UPPER 
JAW 



EXPLOSIVE 
CUTTER 

BOTTOM 





TYPICAL 
JAW (6) 



CABLE-END 
PRELOAD 



HOUSING ATTACHED 
TO SENSORY RING 
FRAME 



HINGE 



LOWER JAW 
EXPLOSIVE 



HINGE 



Figure 12-2, Separation and Unfold Subsystem Mechanical Details 



12-3 



to 



n, 



REG, BUS 0"-»- 



FUSED 

REG. BUS **" 



FUSED o^ 

REG. BUS 



SEP, 
SW, 1 



.^ 



' o- 



K^ 



r 



1 



^> 



SEP. 

Ll"_^_. 



UNFOLD 
TIMER 
TEST 
PLUG 



PRIMARY 

COMMAND 

ENABLE 



REDUNDANT 
COMMAND 
ENABLE 



XXU 



N.C. |>. 



ct 



L->'i>— I 






(FLIGHT) I 



AGE 

TEST 
PLUG 



■^^ 



L 



■^ 



I 

i 
I 

-Of 



I 

(LIMIX. 
SWITCH 



PADDLE UNFOLD 
MOTORS 



SEPARATION 

T/M 



3! 



- P/tf SIGNAL TO 
CONTROLS TIMER 



UNFOLD] 
TIMER 

T/M 



.5-SEC PRMARY 

UNFOLD 

TIMER 

T 



-^ 



.^^ RESET VOLTAGE 
TO CONTROLS S/S 



-O FUSED REG. BUS 




I 






SQUIB 
ARM T/M 



< — -AAa»»^ 



-V\^r" 



i-- 



i^ 



L_l 



UNREG. 
BUS 




Zi 



UNFOLD -■- 
TIMER 2 T/M 



5-SEC BACKITP 
UNFOLD 
TIMER 



Figure 12-3, Separation and Unfold Subsystem Functional Block Diagram 



SECTION 13 
ELECTRICAL INTERFACE SUBSYSTEM 



SECTION 13 
ELECTRICAL INTERFACE SUBSYSTEM 

The EIS is a collection of three modules: The Auxiliary Processor Unit (APU) (See Figure 
13-1 for functional block diagram); The Power Switching Module (PSM) (See Figure 13-2 
for fimctional block diagram) and the Interfece Switching Module (ISM). Together they per- 
form a variety of electrical interfiacing functions including: power switching, telemetry 
signal generation, switching logic, power fusing, signal switching (Data) time code processing, 
automatic "shut-off timers. 

The EIS contains a variety of telemetry points all of which are associated with other subsystems 
and have been discussed in those sections. 

The Launch mode of the APU is given in Table 13-1. 

Table 13-1. APU Launch Mode 





Mode 


Cmd 


POWER 


ON 


656 


MOD 


STBY 


050 


P/L TIMER 


DIS 


720 


SEARCH TRACK 


NORM 


631 


USB/ WP A TIM 


EN 


755 



All EIS fiinctions which were exercised during launch and activation were executed and con- 
firmed. After launch power switching was held to a minimum. Operation of time code pro- 
cessing, search track data processing, back-up timer operation, signal switching and power 
switching was confirmed as commands were executed. 






13-1 



to 

r 

to 




SEARCH TRACK 
PATA 



SEAftCH TftACK 
DATA 



*»WH ON it6 



<^H QIM S)G 



FIBV 
CCC 



SEARCH TRACK A 



SEARCH TRACK fi 



AW PWR SUPPLY 



ie»"SEC 

TIMf A 



1«30-5tC 

TIMt B 



MSS 

TIME CODE 



RBV 
TIME COOE 



SEARCH TRACK P*-TA <D^> 



TLM mTERQGATE SIG <A|> 



TLM inTrnOGATE SPG 



iiSL 



TLM CtOCKiNG SiG !Cif 



SFARCH TflACK DATA 



ri.M INTEKOGATE SiG 



TLM INTEftDGATE SiG 



TLM CLOCKING SIG 



USayPAPWR 



PAVLnAD PIMA 



CON T AOL 
TLM 



ENVELOPE SIG 



MUX 



TELEMETRV 

PROCESSOR 



Figure 13-1. APU Functional Block Diagram 



UNREG BUS 

<PCM) 



FUSE BLOW I 

^AP 8 INPUTS 

ISM) 



REG BUS 
IPRM) 



REG BUS I 

(PRM) 



REG BUS 

(PRM) 



REG BUS 

(PCM) 



BATTERY 

BUS ^ _ 
(SMI 8 'NPUTS 



REG BUS 
(PRM) 




PRM 

a. Unreg Pwr 

b. Fuse Blow 
Bus 



WBVTR#1 



WBVTR#2 



RBV 

a. Electronic 

b. Shutter Ph 

c. Mag Comp, 



4< OUTPUTS 

11 MSS 



a. Mux 

b. Scanner 

C. Scan Motor 



ORBIT ADJUST 
Solenoid Control 



SPARES 



Figure 13-2, PSM Functional Block Diagram 



13-3/4 



SECTION 14 
THERMAL CONTROL SUBSYSTEM 



SECTION 14 
THERMAL CONTROL SUBSYSTEM 

Thermal control of the spacecraft is required in order to provide a mounting surface tempera- 
ture of 20 + 10 C for all equipment mounting internal to the spacecraft. The LANDSAT-2 
spacecraft is composed of three separate elements; the solar arrays, the Attitude Control 
Subsystem and the sensory ring. These elements are thermally decoupled such that the en- 
vironment for mission support and pay load equipment is provided by the sensory ring Thermal 
Control Subsystem. The subsystem is composed of both semipassive and passive elements. 
The semipassive elements are shutters and heaters. Shutters are located on each of the 18 
peripheral compartments and are actuated by tv^o-phase fluid-fill bellows assemblies. The 
heaters are energized by ground command. Passive control, in the form of insulation aad 
coatings, works in conjunction with the semipassive elements to maintain the thermal balance 
of the vehicle. Figure 14-1 is a block diagram of the Thermal Control Subsystem. 

In LANDSAT-2 the thermal control ftinctions were balanced prior to launch and maintained 
their balance, within expected tolerances, throughout powered flight and orbital operations. 

The thermal subsystem in both the sensory ring and the ACS performed within expected limits 
at all locations. 

^ Typical average temperatures were: ACS baseplate 20. 5*^C; sensory ring 18. 9^C; and center 
section 19p 3 C. The shutter position average at Orbit 50 was 42. 8*^. 

Table 14-1 provides typical average telemetry values for the Zener modules obtained during 
thermal vacuum testing and early flight operations. 

In Orbit 2 compensation loads 1, 2, 3, 4, 5, 7 and 8 were turned on as scheduled to provide 
more even heating of the spacecraft until normal operation began. All compensation loads 
except 6 remained on thmi Orbit 50. 



14-1 



HEAT RADIATED FROM HEAT RADIATED FROM 

ACTIVE CONTROLLERS \Qq) ' PASSIVE VEHICLE SURFACES (Qp) 



ANALOG SIGNALS TO T,'M 
SUBSYSTEM 



Q = (T, T) 



1 — \ 



Q = Q (T) 



T/M 
THERMISTORS 



T/M 
CONVERSION 
MODULES (3) 




a^a (r) 



EARTH FLUX {E} 



6 x A X E 



GROUND 
COMMAND 



COMPHNSATiON 
HEAT 
LOADS 




EFFECTIVE EM1SSIV1TY 




SENSOR 

PRESSURE 

(PI 



0=0 [p\ 



SHUTTER 

ANGLE 
(0\ 



31 



T/M 

SHUTTER 

POSITION 

INDICATORS 



Figure 14-1. Functional Block Diagram of Thermal Control Subsystem 



Table 14-1. Thermal Telemetry Values 



Function 
No. 



7080 
7081 
7082 
7083 
7084 
7085 



Function Name 



TLM Conv. Mod. Ql Thermistor Zener 
TLM Conv. Mod. Q2 Thermistor Zener 
TLM Conv. Mod. Q3 Thermistor Zener 
TLM Conv. Mod. Ql Shutter Zener 
TLM Conv. Mod. Q2 Shutter Zener 
TLM Conv. Mod. Q3 Shutter Zener 



Unit 



VDC 
VDC 
VDC 
VDC 
VDC 
VDC 



Average Values 



Orbit 
0-1 



4.85 

4.88 

5.02 

4.95 
4.96 

5.14 



25 OC* 
Plateau 



*Thermal Vacuum Test Data 



14-2 



OF POOR QU^^"^ 



4.85 
4.90 
5.03 
4.95 
4.96 

5.15 



Orbit 

50 



4.86 
4,90 
5.05 
4.97 
4.99 

5.17 



SECTION 15 
NAREOWBAND TAPE RECORDER (NBTR) 



SECTION 15 
NARROWBAND TAPE RECORDER (NBTR) 

The NBTR consists of a single-track recording mechanism and the associated electronics 
necessary for proper amplification and filtering of the RECORD and PLAYBACK signals and 
for control of the record mechanism. The recorder Is completely contained in one box. 

The NBTR records 1 KBPS data from the Telemetry Processor, and, upon command, plays 
back the stored data with simultaneous outputs to the VHF Transmitter and to the Premodula- 
tion Processor, The playback speed is 24 times the record speed, and the output data rate 
is therefore 24 KBPS, The NBTR erases the tape immediately after playback. 

The recorder has a capacity for recording 210 minutes of data, and stops automatically 
when it reaches end-of-tape. Plyaback is accomplished on command, effecting a reversal 
in tape direction at 24 times the record rate. Playback can be commanded at any time before 
the recorder reaches end-of-tape. 

The IiANDSAT"2 spacecraft contains two Narrowband Tape Recorders, providing a total 
sequential recording capability of 420 minutes. A simplified block diagram of the Narrow- 
band Tape Recorder is given in Figure 15-1, 

The Narrowband Tape Recorders were launched in the record mode as shown in Table 15-1. 

The launch mode was verified from telemetry on the CRT display and on the strip charts. 



Table 15-1. 


Narrowband Tape Recorders Launch Mode 


NBTRl 
NBTR 2 


MODE 


CMD 


REC 
REC 


543 
601 



15-1 



I 
to 



O O 

^63 



COMMANDS 



-24.5 V. PR I. PWR. 



1 kBPS BIPHASE DATA 
FROM TLM PROCESSOR 



TELEMETRY 



1 kBPS DATA 



-24.5V. PRI. PWR. 



COMMANDS 



NARROW BAND TAPE RECORDER #1 



CONTROL 
LOGIC 



f 



FILTER 



XTAL OSC. 

175.104 kHZ 



RECORD SIGNAL 



COUNTDOWN 

CHAIN & 
MOTOR LOGIC 
1- 



PLAYBACK SIGNAL 



" + 17 V. 



DC/DC 
CONVERTER 



17 V. 



+ IS V. 



15 V. 



Hi 



AL 



nnD/ 




REEL 



PB EOT _^j- 

SENSORS ^- 



VOLTAGE 
REGULATOR 



+12 V. REC 



" 12 V. REC 



+ 12 V. PQ 



12 V. PB 




RECORD 
AMPLIFIER 



RECOR 



OUTPUT #2 
DRIVER 



FILTER 



F 



I TO VHF 

) TRANSMITTER 



OUTPUT #1 
DRIVER 



PLAYBACK 
PREAMPLIFIER 
AND AMPLIFIER 



KM 



PLAYBACK 



ERASE •^T^ 
{PB ONLYy *3 

REC. EOT 
SENSORS »^ 




REEL 



O > 
O < 



1 



HEADS 



J 



J. 



z\ 



TO PREMODULATION PROCESSOR 



OUTPUT #2 OUTPUT #1 

NARROWBAND TAPE RECORDER #2 
(SAME AS NBTR #1) 



Figure 15-1. Narrowband Tape Recorder Block Diagram 



Initial Turn ON 

Prior to launch on January 22, 1975, NBTRl was put in record at 17:28:37Z and NBTR2 was 
put in record at 12:23:51Z. In Orbit 1 at Alaska, NBTR-1 was played back at 16:26:00 and re- 
turned to the Record mode at 19:33:04. NBTR'-2 was played back at 21:06:58 and returned to 
Record at 21:13:09 to take its turn alternating with NBTR-1. Thereafter the recorders were 
alternated in the RECORD mode, and performed their PLAYBACK generally after 1 minute 
of overlap of the two recorders in the RECORD mode* 

Table 15-2 gives the record history for subsequent orbits. 

Table 15-3 shows typical telemetry values. All are nominal. 

Table 15-4 shows the pre -launch performance of the NBTR's. 



15-3 



Table 15-2. LANDSAT-2 NBTR Record Times 



ORIGINAL PAGE IS 
OF POOR QUALITY 



P/B 
Orbft 


Nbr. 


Start Time 


FME 


End Time 


FME 


% 
Smooth 


% 
BAP 


STA 









022:17:29;03 


001 


19:18:39 


412 


0.39 


0,24 


A 




1 


A 


022:17:24:15 


001 


19:33:03 


484 


0.40 


0,21 


lA 




2 


B 


022:20:06:07 


001 


21:13:19 


253 


0.81 


0.98 


2A 




3 


A 


022:,21:13:35 


001 


22i51:4:i 


369 


0.09 


0. OO 


A 




4 


B 


022:.22:51:43 


001 


00:30:39 


372 


0.04 


0.00 


A 




G 


A 


023:00:30:23 


001 


01:56:15 


325 


6.35 


6.17 


N 




6 


B 


023:01:56:15 


001 


03:49:35 


426 


3.29 


3.15 


A 




7 


A 


023:03:49:35 


001 


05:30:55 


361 


6.82 


6,62 


A 




6 


B 


023:05:30:55 


001 


07:15:11 


392 


0,68 


0.01 


A 




9 


A 


023:07:15:11 


001 


08:58:55 


390 


0.07 


0.07 


A 




10 


B 


















11 




















12 


A 


023:08:58:39 


001 


12:26:39 


781 


10.0 


9,82 


N 




n 


B 


023:12:26:23 


001 


15:52:15 


773 


0.07 


0,00 


N 




14 


A 


023:15:51:59 


001 


17:49:51 


443 


0.63 


0. SI 


G 




15 


B 


023:17:49:35 


001 


19:31:43 


384 


0.07 


0.00 


A 




X6 


A 


023:19:31:27 


001 


21:13:35 


384 


0.24 


0.17 


A 




17 


B 


023:21:13:35 


001 


22:55:43 


384 


18.28 


18.28 


A 




18 




















19 


B 


024:00:25: 19 


001 


01:59:11 


353 


0,08 


0.00 


A 




20 


A 


024:01:59:27 


001 


03:54:39 


433 


0.44 


0.30 


A 




21 


B 


024:03:54:23 


001 


05:37:03 


386 


0,07 


0,00 


A 




22 


A 


024:05:36:47 


001 


07:21:19 


393 


0.07 


0,01 


A 




23 


B 


024;07;21:03 


001 


09:05:03 


391 


0.07 


0. 00 


A 




24 




















25 




















26 


A 


024:09:05:03 


001 


12:33:03 


781 


0.06 


0.00 


N 




27 


B 


024:12:32:47 


001 


15:52:47 


751 


0.07 


0.00 


N 




26 


A 


024:15:52:31 


001 


17:55:27 


462 


0.09 


0.00 


A 




29 


B 


024:17:55:27 


001 


19:37:03 


382 


0.07 


0.00 


A 




30 


A 


024:19:35:59 


001 


21:19:59 


391 


0.16 


0,00 


A 




31 


B 


024:21:19:11 


001 


23:01:51 


386 


0.06 


0,00 


A 




32 


A 


024:23:01:35 


001 


00:43:59 


385 


0.31 


0.24 


A 




33 


B 


025:00:43:43 


001 


02:08:47 


320 


0.00 


0.00 


N 




34 


A 


025:02:08:31 


001 


04:00:47 


422 


0,05 


0.00 


A 




35 


B 


025:04:00:31 


001 


06:08:47 


482 


0,21 


0.00 


A 




36 


A 


025:05:39:27 


001 


07:25:51 


400 


0.70 


0.02 


A 




37 


B 


025:07:25:35 


001 


09:05:35 


376 


0.05 


0.00 


A 




38 




















39 




















40 




LOST 
















41 


B 


025:12:34:07 


001 


15:37:51 


690 


0.06 


0.00 


N 




42 


A 


025:15:37:51 


001 


17:52:31 


506 


0.03 


0,00 


A 




45 


B 


025:17:55:27 


001 


19:37:19 


383 


0.24 


0.24 


A 




44 


A 


025:19:37:19 


001 


21:19:59 


386 


0.29 


0.25 


A 




45 


B 


025:21:19:43 


001 


23:01:51 


384 


0.35 


0,29 


A 




46 


A 


025:23:01:51 


001 


00:30:23 


333 


0.05 


0.00 


N 




47 


B 


026:00:30:23 


001 


02:09:03 


371 


0.05 


0,00 


N 




48 


A 


026:02:09:03 


001 


04:05:35 


438 


0.05 


0.00 


A 




49 


B 


026:04:03:11 


001 


05:41:19 


369 


0,07 


0.00 


A 




SO 


A 


026:05:41:19 


001 


07:26:39 


396 


0.05 


0.00 


A 





15-4 



Table 15-3. Narrow Band Tape Recorder Telemetry Values 







* 
T/V 








Value 




Func. 




2QPC 


Orbit 


No. 


Name 


Plateau 


36/37 


10001 


A- Motor Current (ma) 








Record 


128 


132.0 




P/B 


107 


108.0 


10101 


B^ Motor Cvirrent (ma) 








Record 


153 


148.5 




P/B 


149 


143.6 


10002 


A-Pwr Supply Cur, (ma) 








Record 


185 


170,5 




P/B 


425 


410 


10102 


B-Pwr Supply Cur. (ma) 








Record 


260 


260 




P/B 


480 


481 


10003 


A-Recorder Temp (DGC) 


30.7 


26.1 


10103 


B-Recorder Temp (DGC) 


28,5 


27.0 


10004 


A-Supply Volt 


24.9 


24.87 


10104 


B-Sv5>ply Volt 


24.6 


24,55 



^Thermal Vacuum Test Data 



Table 15-4. Pre-Launch Performance of the Narrowband Tape Recorder 





Components 

NBTR 1 EAB-QMl 

NBTR 2 EAB-FT4 








Pre- 


-Launch Performance 










Parameter Spec 


NBTRl 


NBTR 2 




Record Time >210 min 


216. 5 min 


216 


min 




Data quality judged by brush recorder outputs 
synopsis - quality good 


and 


computer 



15-5/6 



SECTION 16 
WIDE BAND TELEMETRY SUBSYSTEM 



SECTION 16 
WIDE BAND TELEMETRY SUBSYSTEM 

The Wide Band Telemetry Subsystem (WBIS) consists of two 10/20 watt S-Band t^M Tr^s- 
mitters and associated filters, antennas, and signal conditioning equipment. The subsystem 
is used to transmit Return Beam Vldicon (REV) video data and Multispectral Scanner (MSS) 
digital data to LANDSAT ground stations* The RBV and MSS data can be transmitted in real 
time as It is being generated, or recorded on either of two Video Tape Recorders (or both) 
and played back through the WBTS when in view of a ground station. A Functional Block 
Diagram is shown in Figure 16-1 and the physical configuration is illustrated in Figure 16-2. 

The WBTS was launched in the OFF mode and in the configuration shown in Table 16-1, Ver- 
ification of this mode was obtained in the telemetry from Madrid and Alaska playback early 
in Orbit 1. The Check Compare (Table 8) on the CRT verified there were no exceptions to 
the commanded configuration. 

Initial Turn-ON 

The Wide Band Telemetry Subsystem was initially turned on in the 10 watt mode in Orbit 12 
while over Greenbelt/Merritt Island* At 14j29:3l both wide band power amplifiers were 
turned on together, with Inverter A dN at 14:29:41, Filters A and B were both inhibited to 
allow only the unmodulated carrier to radiate* 

The power amplifiers were both turned OFF at 14:36:53 and inverter A turned OFF at 
14:36:55* All telemetry values were nominal as shown in Table 16-3. 

Table 16-1, Wide Band Telemetry Subsystem Launch Mode 



WBPAl, 2 EN 


Mode 


CMD 


PRIME/RED 


776/754 


WBPAl 


OFF 


561 


OUTPUT SEL 1 


LO 


541 


WBPA2 


OFF 


067 


OUTPUT SEL 2 


LO 


047 


RBV Bias 


A 


546 


DATA WBPA 


PRIME 


705 



16-1 



OS 
to 



2 o 
^63 



VIDEO 
TO 3. 5 MHz 



RBV 
SUBSYSTEM 



WIDEBAND 

VTR 
SUBSYSTEM 



MSS 
SUBSYSTEM 



WIDEBAND 

FREQUENCY 

MODULATION 

AND 

POWER 

SUPPLY 



2229. 5 MHz 



WIDEBAND 
POWER 

AMPLIFIER 
NO. 1 



WIDEBAND 
POWER 

AMPLIFIER 
NO. 2 



2265, 5 MHz 



PCM-NRZ 
15 MbpS 



OUTPUT 
FILTER 
NO. 1 



OUTPUT 

FILTER 

NO. 2 



I POWER OUT 
I 




J 



20 WATTS 

OR 
10 WATTS 



GROUND 
STATION 



Figure 16-1. Wideband Telemetry Subsystem Block Diagram 








j| 1^ VVtt^lMND POWER SUPPLY 






I GENERAL ©UfCTfllC 



WIDEBAND FlitQUENCY MODULATOS 



it Mi* At i^ ll^ClStt 



1 




WIDEBAKD POWER AMPilEIER 






Figure 16-2. Wideband Telemetry Subsystem 



Subsequent Operations 

In Orbit 13 both power amplifiers were operated in the 20 watt mode with both filters in- 
hibited. The sequence of events is shown in Table 16-2, 

Wide Band Power Amplifier-1 was subsequently operated in Orbits 41, 46 and 47, WBPA-2 
was subsequently operated in Orbits 19, 26, 27, 28, 42. 46 and 47. The entire subsystem 
operated normally throughout these orbits, as shown in the telemetry values of typical 
orbits shown in Table 16-3, 

Prelaunch subsystem performance is shown in Table 16-4. 



16-4 



Table 16. 2 Operations of WPA 




WBPA-1 


CMD 


WBPA-2 


16:10:39 


Power ON 


16:10:37 


16:10:41 


Inverter ON 


16:10:41 


16:13:56 


Sel 20 watt output 


16:14:15 


16:17:55 


Power OFF 


16:17:53 





Table 16-3. Wide Band Telemetry Subsystem 






(1) 


t 

Name 


T/V (2) 


Telemetry Values 


low 


20W 


low 


20W 


Orbit 16 


Orbit 47 


12001 


Temp, TWT Coll. (DGC) 


30.1 






33.6 


28.14 


34.38 


12101 




27.9 






31.2 


25.93 


30.00 


12002 


Cur, Helix (MA) 


3.30 






3,85 


3.20 


4.29 


12102 




4.03 






4,56 


4.28 


4.41 


12003 


Cur, TWT Cath. (MA) 


33.20 






46.10 


32,77 


46.04 


12103 




34.09 






46.78 


33.93 


46.42 


12004 


Fwd Power (DBM) (3) 


40.61 






42.68 


40.61 


42.83 


12104 




40.93 






43.71 


41.01 


43.81 


12005 


Refl Power (DBM) (3) 


22.34 






27.0 


21.11 


26.50 


12105 




34.55 






36.45 


36.03 


37.50 


12227 


Con. Volt, Loop Stress (MHz) (4) 




1.54 




1.80 


2.14 


12228 






2.53 




1.48 


1.51 


12229 


Temp. Mod (DGC) 




19.5 




19.00 


18.51 


12232 


+15 VDC Pwr Sup (TMV) (5) 




2.65 




2.65 


2.65 


12234 


-15 VDC Pwr Sup (TMV) (5) 




4.07 




4.20 


4.27 


12236 


+5 VDC Pwr Sup (TMV) (5) 




3.55 




3.55 


3.57 


12238 


-5 VDC Pwr Sup (TMV) (5) 




4.08 




4.17 


4.20 


12240 


-24 VDC Unreg. Pwr (TMV) (5) 




5.86 




5.88 


6.20 


12242 


Temp, Inv. (DGC) 

1 




23.7 




23.42 


24.12 



NOTES: 



(1) Function numbers for WPA-1=120XX; for WPA-2= 

(2) Thermo-VacuTim Test data for comparison 

(3) Pwr outputs of 10 or 20 watts can be selected 

(4) Any reading other than zero or -7.5 is acceptable 

(5) Oniy power supply A operated during these orbits 



121XX 



16-5 



Table 16-4. Wideband Telemetry Subsystem 



Components 


S/N 


Wideband Power Supply 
Wideband Frequency Modulator 
Wideband Power Amplifier (2) 
Wideband Filter (2) 


6549508 
6549505 

FT 3 & FT4 
4 & 8 


Pre- Launch Performance 












Spec 


Measured 


Modulator A Freq. Stab. 




2229. 5 MHz 
±335 KHz 


2229. 5 MHz 
+0 KHz 
-270 


Modulator B Freq. Stab. 




2265. 5 MHz 

±338 KHz 


2265. 5 MHz 
+0 
-280 KHz 


Power Amp No. 1 Output* 


High 
Low 


+40. 6 DBM 
+37.6 DBM 


+41.3 DBM 
+38. 6 DBM 


Power Amp, No. 2 Output* 


High 
Low 


+40. 6 DBM 
+37. 6 DBM 


+40. 8 DBM 
+37. 8 DBM 




PROBLEM SUMMARY 




Problem 








• Jumps in helix current telemetry 
seen in both WBPA's. 

WBPA 1 - 1. 1 MA 

WBPA 2 - 0. 65 MA 


• No degradation of performance 
observed. WBPA's in LANDSAT-i 
also show helix current telemetry 
jumps (once per 2 or 3 transmissions). 


EBPR435, 9/3/74 








EBPR 520, 10/17/74 









♦Includes 2 DB transmit circuit loss 



16-6 



SECTION 17 
ATTITUDE MEASUREMENT SENSOR (AMS) 



SECTION 17 
ATTITUDE MEASUREMENT SENSOR (AMS) 

The AMS is a passive radiometric balance sensor which operates in the 14 - 16 micron 
IR Band. This band pass was selected to take advantage of the earth's horizon predictabi- 
lity in the 14-16 micron region, and to improve the off-null accuracy by ground based cor- 
rection. The entire earth disk is imaged by a germanium lens to a focal surface containing 
four light pipes (four field of view sectors). See Figure 17-1 for functional block diagram, 
and Figure 17-2 for hardware illustration. AMS Telemetry Values are shown in Table 17-1. 



The AMS was launched in the OFF mode (CMD 774), turned ON during Orbit 6 and has been 
performing normally since tiien. 



Table 17-1. AMS Telemetry Values 



Function 
No. 




Units 


Average Value 


Orbit 7 


20°C Plateau 


Orbit 50 


3004 
3005 


Case - Temp 1 
Assembly - Temp 2 


"'c 

OC 


15.74 
15.28 


20.9 
20-5 


19.00 
18.70 



17-1 



-1 

J 
to 



PITCH 

DETECTOR 

ARRAYS 



ROLL 

DETECTOR 

ARRAYS 



MOS FET 
CHOPPER 
NETWORK 



. I 



PITCH 
AMP 



-O 



PITCH OUTPUT 
AMPLIFIER 



PHASE 
DETECTOR 



ROLL 
AlVlP 



1> 



30-HZ 
GENERATOR 




JTH> 



ROLL OUTPUT 
AMPLIFIER 



PHASE 
DETECTOR 




r^ 



TEMP. TELEMETRY 
CIRCUITS 



PITCH SIGNAL 
AMPLIFIER TEST 



^ + PITCH OUTPUT 



- PITCH OUTPUT 



+ ROLL OUTPUT 

- ROLL OUTPUT 

ROLL SIGNAL 
AMPLIFIER TEST 

2 TEMP OUTPUTS 
PHASE 1 TEST 



^ PHASE 2 TEST 



+12 V REG. 



-12 V REG. 







































+12 V 
REG, 






DC-DC 
CONV. 


































-12 V 
REG. 



















-12 V TEST 



- +12 V TEST 



VEHICLE 
POWER 
INPUT 
-24.5 VDC 



Figure 17-1, AMS Block Diagram 



o o 



:^^mf:mmtMmf.^^^<^^m^Wt^^'^' 



8 






.'»*>* 



•-^'-v^.^. 








Figure 17-2, Attitude Measurement Sensor 



SECTION 18 
WIDEBAND VIDEO TAPE RECORDERS (WBVTR) 



SECTION 18 
THE WIDEBAND VIDEO TAPE RECORDERS (WBVTR) 

The Wideband Video Tape Recorder (WBVTR) Subsystem is comprised of two rotating-head, 
magnetic tape recorders, each housed in two enclosures: (1) a pressurized housing for the 
Transport Unit (TXJ) and; (2) an unpressurized enclosure for the Electronics Unit (EU), The 
TU includes the transport mechanism, the video head wheel, record amplifiers, playback 
pre -amplifiers, and transport controls. The EU includes the record and playback formatting 
circuitry, the voltage converter » motor control circuits and command and control circuits. 

The primary function of either WBVTR is to selectively record, store, and playback analog 
data from the Return Beam Vidicon (RBV) cameras or digital data from the Multispectral 
Scanner (MSS) Subsystem. Additional record and playback channels are provided on the 
tape. These include a prerecorded Search Track Signal for providing tape position informa- 
tion, an Auxiliary Track for recording PCM telemetry data, and a servo control track for 
playback speed control. A transverse recording technique utilizing four rotating heads is 
used for Wideband RBV and MSS data* The narrowband data, (servo control, PCM data, 
and search pattern) are recorded longitudinally with fixed heads. See Figures 18-1 and 
18-2 for functional block diagrams* . Figures 18-3, 4 and 5 show physical configuration. 
The launch and activation evaluation follows. 

LAUNCH MODE 

The Wideband Video Tape Recorders 1 and 2 (WBVTR-1 and 2) were launched in the mode 
shown in Table 18-1 • This launch mode was verified by OCC during prelaunch checkout at 
WTR, and subsequently by narrow band recorder playback from Alaska. 



18-1 



00 

I 
to 



PCM DATA IN 



PCM DATA OUT 



RBV VIDEO IN 



MSS DATA (N 



MSS CLOCK IN 



RBV VIDEO OUT 



MSS DATA OUT 



MSS CLOCK OUT 



> 



<■ 



> 



> 



<- 



<- 



SEARCH TR 



K. OUT ^ 



50 KHZ IN 



RBV RUN TAPE 

SIGNAL IN 

RBV REPHASE 
SIGNAL OUT 



> 



> 



COMMANDS 



PCM P/8 
SIGNAL PROC 



PCM RECORD 
SIGNAL PROC. 



RECORD 



■♦*■ 



MSS 

RECORD 

-SIGNAL 

PROC. 



RBV RECORD 
SIGNAL PROC 



J 



TELEMETRY 



MSS 

PLAYBACK 

SIGNAL 

PROC. 



RBV P/B 
SIG. PROC. 



PLAYBACK 
PREAMP 



REFERENCE 
GENERATOR 



20 KHZ 

OSC/AMP 



DRIVE 

CONTROL 

SIGNAL 

PROC, 



■B 



AUX. TRK. HEAD 



RECORD AMPL. 
& CURRENT ADJUST 



(—1 "w 

s ^ 



ROTATING 
TRANSFORMER 



D 



(4) R/P HEADS 



SEARCH 
TRACK 

SIGNAL 
PROC. 



"■ [3 
— D 

-o 



y SEARCH TRK. HEAD 



0" SEARCH TRK. HEAD 



CONTR. TRK. HEAD 



TONE WHEEL 



•W^ JMOTOR DRIVES 



--# I 



■B 



PLAYBACK 



Figure 18-1. WBVTR Functional Block Diagram 



^ O 

Is 



IkBPSDATA 



RETURN 
BEAM 
VIDICON 
SUBSYSTEM 



(AUXILIARY CHANNEL) 



VIDEO 



RUM SIGNAL 



RUN SIGNAL 



REPHASING 



MULTISPECTRAL 
SCANNER 

SUBSYSTEM 



RUN 
SIGNAL 



1 kBPS DATA 



(AUXILIARY 
CHANNEL) 



WIDEBAND 
SUBSYSTEM 



POWER 
SUBSYSTEM 



COM- 



MANDS 



SO 
kHz 



COMMAND 
CLOCK 



COMMANDS 
■34,5V 



00 
I 

GO 



Figure 18-2. WBVTR Block Diagram 



I 



§ 



o 

O " 

O 






^ 




Figure 18-3. Wideband Video Tape Recorder 




Figure 18-4, Wideband Video Tape Recorder 




ERAse HEAtt 



!W MOTOR 



NEG*ATOH 
DIFFEREMTIAL 



TAPE GUIDE 



HEADWHEEL 
PANEL 



CAPSTAN 



LONGITUDINAL 
MEAD 



CAPt> IAN 
MOTOR 



Figure 18-5. WBVTR Transport 



OHIGINAL PAGE IS 
OP POOR QUALITY 



18^5 



Table 18^1. Launch Configuration 



WBVTRl 


Mode 


Cmd 


OFF 


651 


WBVTR 2 


OFF 


712 


RBV STBY 


1 


464 . 


MSS STBY 


2 


572 


VO PROT 2 


EN 


554 


VO PROT 1 


EN 


467 


SEARCH TRA 


NORM 


563 


WBVTR-1 


TAPE POSITION 


900 


WBVTR-2 


TAPE POSITION 


919 



ACTIVATION 

Initial activation of the WBVTR subsystem occurred in Orbit 5. Both recorders were 
rewound from their launch position near mid-tape for a duration of about 2 minutes. 
The applicable series of commands are shown in Table 18-2. The footage count of 
WBR-1 went from 900 to 423; the WBR-2 footage went from 919 to 423. 



Table 18-2. Series of Commands for Initial Activation of WBVTR 

Orbit 5, 23 January 1975 



Time 


Cmd 


Activity 


01:59:08 


650 


WBR-2 ON Prime 


01:59:10 


572 


WBR-2 STBY MSS 


01:59:15 


607 


WBR-1 ON Prime 


01:59:17 


464 


WBR-1 STBY RBV 


01:59:22 


465 


WBR-1 FAST R/W 




552 


WBR-2 FAST R/W 


02:01:06 


071 


APU Norm Mode 


02:01:17 


572 


WBR-2 STBY MSS 


02:01:19 


464 


WBR-1 STBY RBV 


02:01:20 


712 


WBR-2 OFF 


02:01:21 


651 


WBR-1 OFF 



18-6 



SUBSEQUENT OPERATIONS 

Table 18-3 shows the subsequent use of the WBVTR subsystem. All operations were nominal. 
Telemetry values and MESE counts are normal and are shown in Tables 18-4, 18-5, and 
18-6. All values are nominal* 

Tables 18-7 and 18-8 show the prelaunch performance of the WBVTR. Table 18-8 lists 
the components and ground operating time. 

Table 18-3. History of WBVTR Use 



Mode 


Orbits 


WBR-1 


WBR-2 


Record 


40, 41 


19, 21 


Rewind 


5, 16, 17, 34, 46 


5, 16, 17, 26, 31, 46 


Playback 


15, 17, 33 & 47 (pre-launch recorded) 
46 (rec. at RBV activation) 


15, 17, 46, 47 (recorded pre-launch) 
26 (MSS sun cal) 



Table 18-4. WBVTR Telemetry Values 



WBVTR-1 Fuactlone 


Telemetry Values In Orbtts 




Name 


T/V 


ORB 45/46 


13022 


Pressure, Traas 


<PSI) 


16.46 


16.52 


1S02S 


Temp Trans 


(DgC) 


19.1 


20.74 


13024 


Trnnp Elec 


PffC) 


31.8 


25.00 


15032 


Um Volt Out 


(VPP) 


1.47 


1.48 


13034 


+5, 6 VDC Conv 


(VDC) 


5.54 


5,70 


13200 


-24, 5 VDC 


(VDC) 


NA 


1.82 


18201 


-12 VDC 


(VDC) 


NA 


2,44 


13202 


Temp APU 


(DgC) 


NA 


29.06 



WBVTR-2 Functions 


Telemetry Values In Qrbita ' 




Name 


T/V 


ORB 45/46 


13122 


Pressure^ Trans 


(PSI) 


16.22 


16.12 


13123 


Temp Trajis 


(DgC) 


18.9 


21.50 


13124 


Temp Elec 


(UgC> 


31.2 


23,50 


13132 


Urn Volt Out 


(VPP) 


1.3 


1.30 


1S134 


+5,6 VDC 


(VDC) 


5.57 


5.71 


13200 


-24, 5 VDC 


(VDC) 


NA 


1.82 


13201 


-12 VDC 


(VDC) 


NA 


2.44 


13202 


Temp APU 


(»gC) 


NA 


29.06 



NA = not avBllable 



18-7 





Table 18-5. Function Values by Mode in Orbit 




WBVTR-1 








Function/Desc ription 


T/V 


ORB 31/46 


13029 


- Input P/B Voltage 








Record 


0.0 


0.0 




Playback 


0.57 


0.60 




Rewind 


0.0 


0.0 




Standby 


0.0 


0.0 


13028 


- Capstan Motor Current 








Record 


0.32 


0.31 




Playback 


0.29 


0.26 




Rewind 


0.23 


0,19 




Standby 


0.0 


0.0 


13030 


- Headwheel Motor Current 








Record 


0.50 


0.50 




Playback 


0.495 


0.49 




Rewind 


0.41 


0.44 




Standby 


0.41 


0,45 


13031 


- Recorder Input Current 








Record 


3.58 


3.69 




Playback 


3.92 


3.37 




Rewind 


2.18 


2.23 




Standby 


1.79 


1.78 


13033 


- Servo Voltage 








Record 


0.0 


0.0 




Playback 


49.99 


50.01 




Rewind 


0.0 


0.0 




Standby 


0.0 


0.0 


13026 


- Capstan Motor Speed 








Record 


89.77 


88.61 




Playback 


89.37 


88.35 




Rewind 


100.12 


100.2 




Standby 


0.0 


0.0 


13027 


- Headwheel Motor Speed 








Record 


97.5 


96.72 




Playback 


96.86 


97.28 




Rewind 


98.96 


98.6 





Standby 


99.12 


98.39 



18-8 



oSf "AGE m 



Table 18-6, Function Values by Mode in Orbit 





WBVTR-2 








Function/Description 


T/V 


ORB 31/46 


13129 


- Ii^ut P/B Voltage 








Record 


0.0 


0.0 




Playback 


0.37 


0.35 




Rewind 


0.0 


0.0 




Standby 


0.0 


0.0 


13128 


- Capstan Motor Current 








Record 


0.33 


0.33 




Playback 


0.34 


0.33 




Rewind 


0.16 


0.20 




Standby 


0.0 


0.0 


13130 


- Headwheel Motor Current 








Record 


0.47 


0.47 




Playback 


0.46 


0.48 




Rewind 


0.43 


0.44 




Standby 


0.45 


0.43 


13131 


- Recorder Input Current 








Record 


2.88 


2.90 




Playback 


3.11 


3.14 




Rewind 


1,79 


1.80 




Standby 


1.18 


1.51 


13133 


- Servo Voltage 








Record 


0.0 


0.0 




Playback 


48.92 


49.00 




Rewind 


0.0 


0.0 




Standby 


0.0 


0.0 


13126 


- Capstan Motor Speed 








Record 


108. 66 


112.10 




Playback 


108,38 


112.10 




Rewind 


130. 09 


120.43 




Standby 


0.0 


0.0 


13127 


- Headwheel Motor Speed 








Record 


98.41 


98.08 




Playback 


98.11 


97.04 




Rewind 


99.95 


98.6 




Standby 


101.72 


100. 79 



18-9 



Table 18-7. Pre-Launch WBVTR History 

DATE ACTIVITY 

5/28 ■• 6/12/74 1ST THERMAL VACUUM TEST. VTR 1 - FT 2 VTR 2 » FT 2 

EACH RECORDER SHOWED RISING ERROR RATE DURING 30 MINUTE TESTS, MORE PRO- 
NOUNCED AT HIGH TEMPERATURE. FT 1 ERROR RATE CONSIDERABLY HIGHER THAN FT 2 
ERROR HATE, 



6/16/74 



6/21/74 
7/16/74 



10*^0 


20°C 


3-5 


3-10 


5-75 


3-95 



MINOR FRAME SYNC ERRORS IN TEN SECONDS NEAR BOT & EOT 

VTR PRE TV 20^C 35°C 

FT 2 6-14 12-70 20-85 

FT 1 5-130 10-160 20-480 

OBSERVED CHANGE (HIGHER) CAPSTAN MOTOR CURRENT TELEMETRY IN VACUUM ON FT 2, 

OBSERVED SEVERAL INSTANCES OF SIMULTANEOUS PBOT & SHOT ON FT 2. 

POST TV TESTS 

1. DETERMINE IF FT 1 RECORD CURRENT (1 DB) WAS OPTIMUM - IT WAS. 

2. DETERMINE IF SIMULTANEOUS MSS ERROR BURSTS & AUX TRACK DROPOUTS WERE 
CONTROL TRACK ANOMALY - THEY ARE. 

3. DETERMINE IF SUBSTITUTE TELEMETRY BOARD NORMALIZES CAPSTAN MOTOR 
CURRENT TELEMETRY ON FT 2 - IT DIDN'T 

FT 1 & FT 2 RETURNED TO RCA. 

FT 6 DELIVERED TO GE. TESTS RUN WITH FT 6 IN EACH OF VTR 1 & 2 P06IT[QNB, MSS 
ERRORS VERY LOW IN EACH POSITION. SEARCH TRACK ERRORS NOTED IN 12 PLACES, 



7/23/74 - 7/26/74 
7/29/74 - 7/31/74 

8/2/74 - 8/13/74 

9/28/74 

9/3/74 - 9/10/74 

10/4/74 

10/16/74 - 10/18/74 

10/29/74 - 10/30/74 
10/30 - 10/31/74 



MSS DATA TESTS WITH FT IIN VTR 1 POSITION AND FT 6 IN VTR 2 POSITION. FT 6 
LOW ERROR RATE, FT 1 RELATIVELY LOW, BUT RISING ERROR RATE. (5-30) 

MSS DATA TESTS WITH FT 2 IN VTR 1 POSITION AND FT 6 IN VTR 2 POSITION. FT 2 
SHOWED RISING ERROR RATE ON 3 SUCCESSIVE PLAYBACKS. FT 6 SHOWED LOW ERROR 
RATE WITH SAME DATA. 

SERIES OF TESTS WITH FT 2 AND FT 6 IN FLIGHT SPACECRAFT AS VTR 1 AND 2. AND 
WITH FT 1 ON BIT BOARD. TESTS DISCLOSED PATTERN SENSITIVITY, AND CHARACTER 

OF ERRORS WAS NOTED AND ANALYZED. FT 1 WAS RETURNED TO RCA FQR FURTHER 
ANALYSIS, WHERE MODIFICATIONS WERE DEVELOPED AND APPLIED TO FT 1, 

PRE-THERMAL/VACUUM TESTS. FT 2 SHOWED HIGH AND RISING ERROR RATE DURING 
30 MINUTE TEST (150-450). FT 6 SHOWED GOOD ERROR RATE (5-5). 

SECOND SPACECRAFT THERMAL VACUUM TEST. FT 2 SHOWED RISING ERROR RATE. 
AND HIGH (70-100) AT HIGH TEMPERATURE. FT 6 SHOWED CONSISTENTLY LOW ERROR 
RATE, 

FT 1, WITH MODIFICATIONS, DELIVERED TO GE AND PLACED IN BONDED STOCK, 

SPACECRAFT VIBRATION TEST, VTR l-FT 2. VTR 2- FT 6. DURING SPACECRAFT 
CONFIDENCE TESTS RUN BEFORE, BETWEEN AND AFTER VIBRATIONS, FT 2 SHOWED 
HIGHER ERROR RATE ON EACH SECOND PLAYBACK OF MSS DATA. 

POST VIBRATION 30-MINUTE MSS DATA TEST SHOWED HIGH ERROR RATE (100-230) 
ON FT 2. SECOND AND THIRD PB^S ALSO HIGH. FT 6 GOOD, 

LIMITER/DEMOD BOARDS REMOVED FROM FT 2 EU AND SENT TO RCA FOR SINGLE 
MODIFICATION. BOARDS RETURNED TO GE AND REPLACED IN EU ERROR RATE 
HIGH (150-900). 



11/5 - 11/8/74 
11/9 - 11/12/74 



COMPLETION OF MODIFICATIONS TO FT 2 AT GE. FINAL TESIB SHOWED VERY GOOD 
ERROR HATE WITH NO RISE (5-5). ^^ 

FT 2 EU REMOVED FROM SPACECRAFT FOR VIBRATION AND THERMAL TESOS iUN- 
POWERED) AT RCA. EU BENCH TEST AT GE WITH ENGINEERING MODEL T/V EU " 
INSTALLED ON SPACECRAFT. MSS DATA FROM U/8/74 PLAYED BACK AND NEW 
30-MINUTE RECORD/PLAYBACK TEST RUN. LOW ERROR RATE WITH NO RISE (5-5) 



18-10 



^KJ^AL PAGE IS 
Ql^ f OOR QUALITY 



Table 18-8. Pre-Launch WBVTR Problem Summary 



PROBLEM 

VTR FT-2 CAPSTAN MOTOH CURRENT 
TELEMETRY INCREASED IN VACUUM. 
EBPR271, 5/29/74. 

SIMULTANEOUS AUXILIARY TRACK 
DROPOUT WITH MSS DATA ERROR 
BURST, EBPR 375, 6/11/74 (SN FT-2) 
EBPR 378, 7/15/74 (SN FT-6). 

RISING MSS MINOR FRAME SYNC ERROR 

RATE. 

EBPR'S 097 10/19/74 

124 2/28/74 

133 3/21/74 



RESOLUTION 

• CAUSED BY SATURABLE REACTOR IN TELEMETRY 
CIRCUIT AFFECTED BY VACUUM, RCA REPLACED 
SATURABLE REACTOR. MR D08193. 

# OCCURS RELATIVELY INFREQUENTLY ON ALL 
VTR^S, INCLUDING ERTS A. DUE TO MOMENTARY 
LOSS OF LOCK IN CAPSTAN SERVO LOOP. ACCEPT 
AS IS. MP. D08168 FT 2, MR D08I94 FT 6. 



LONG SERIES OF TESTS AT RCA AND GE RE- 
VEALED SOME PROBLEMS WITHIN VTR'S. RCA 
RECOMMENDED AND MADE MODIFICATIONS TO 

SN FT 1 AND FT 2: 



1. DECREASE RINGING (MAKE HF ROLL OFF 
SMOOTHER) IN MSS PB CIRCUITS. 

2. INCREASE TIME CONSTANT OF DC 
RESTORER. 

3. DECREASE AMPLITUDE OF PILOT TONE 
(1.5 MHZ) SIGNAL IN RECORD CIRCUITS, 
MR D08150 FT 1, MR D08195 FT 2, 



SEARCH TRACK NUMBERS ERRATIC ON VTR 
FT-6. EBPR 377 7/18/74. 



PRESSURE TELEMETRY DROPPED AND 
RETURNED TO NORMAL A FEW MINUTES 
LATER. VTR FT-6, EBPR 462 9/6/74. 

TAPE TRANSPORT UNIT FT-2 TELEMETRY 
INDICATED BOTH PRIMARY AND SECONDARY 
BEGINNING OF TAPE INDICATIONS. 
(5/28/74) EBPR 262, MR D08196. 



ABOUT 20 NUMBERS (OUT OF 3600) SOMETIMES 
READ OUT INCORRECTLY, APPARENTLY DUE 
TO EXTRA BITS (OR NOISE) ON TAPE. IN- 
CORRECT NUMBERS HAVE NO HARMFUL EFFECT 
TO OPERATION SINCE NUMBERS ARE HIGHLY 
REDUNDANT, ACCEPT AS IS. MR D08170, 

POTENTIOMETERS SHOW OCCASIONAL NOISE* 
OCCURRED AI^O ON ERTS A. ACCEPT AS IS. 
MRD08267. 

RETURNED TO CONTRACTOR AND REWORKED, 

CLOSED. 



RBV DATA 

• NO SIGNIFICANT DEGRADATION OF RBV DATA. 
MSS DATA 

• BOTH VTR^S HAVE MSS MINOR FRAME SYNC ERRORS BELOW 10 ERRORS 
IN 10 SECONDS. AVERAGE APPROXIMATELY 5 IN 10 SECONDS, 

• NO SIGNIFICANT RISE IN ERRORS DURING 30 MLKUTE PLAYBACK, 



ORIGINAL PAGF FQ 



18-H 



Table 18-9. WBVTR Components 



• IN SPACECRAFT 

TAPE CONTACT TIME 
(AS OF 11/25/74) 

VTR 1 S/N FT-2 522 HOURS 

VTR 2 S/N FT-6 114.5 HOURS 

• EXPECTED LIFE FOR EACH RECORDER - 1, 000 HOURS 



18-12 



SECTION 19 

RETURN BEAM VIDICON SYSTEM (RBV) 



SECTION 19 
RETURN BEAM VIDICON SYSTEM (RBV) 

Ground scene Information is viewed through three Return Beam Vidlcon (RBV) Camera 
Sensors as they are simultaneously exposed. The RBV sensors convert the scene information 
in three unique spectral bands into low- level analog signals. The Camera Electronics convert 
this information into a video format that is fed to the Camera Controller Combiner (CCC), 
where the three camera videos are combined with sync, blanking, and timing signals and 
with coding information to produce a single composite video format. The Camera Controller 
Combiner controls the operating modes of the cameras and the generation of the composite 
video signal. The cameras may be commanded for single exposure, cyclic exposure, and 
calibration. The composite video signal is either stored on a Wideband Video Tape Recorder 
for later playback, or transmitted in real time through the spacecraft Wideband Telemetry 
Subsystem, An auxiliary video signal from each camera may also be applied directly to the 
Wideband Telemetry System without passing through CCC, See Figure 19-1 for functional 
block diagram, and Figure 19-2 for physical illustration. An equipment list is shown in 
Appendix A. 

The RBV subsystem was launched in the mode shown in Table 19-1. Verificatton of this 
mode was obtained by telemetry early in Orbit 1 at Madrid and later by playback from 
Alaska. 

INITIAL TURN-ON 

The Return Beam Vide con Subsystem (RBV) was first turned ON in Orbit 40 for 1 minute 
and 2 seconds with Camera 1, but was turned OFF before shutter operated. WBVTR-1 was 
in record mode but received no data* All telemetry was nominal. 

The RBV was turned on again in Orbit 41 on 25 January 1975 while over Greenbelt, The 
sequence of activities is shown in Table 19-2, Telemetry (Table 19-3), quick-look pictures, 
and the A- scope of the TR-70 all showed nominal sync pulses and video data. 



19-1 



SUBSEQUENT OPERATIONS 

The RBV was not operated again during this report period; therefore, no RBV scenes are 
available for processing. 

Table 19-4 shows the pre-launch performance of the RBV. 

Table 19-1. Return Beam Vldicon Subsystem Launch Mode 



CALIBRATE 


MODE 


CMD 


EN 


372 


APERTURE CORR 


OUT 


431 


EXPOSURE 


4 


454 


CYCLE 


CONT 


470 


CATH REACT 


OFF 


371 


MAG COMP 


EN 


677 


MAG COMP 


HI 


753 


THER MOD 1 


EN 


770 


THER MOD 2 


EN 


730 


THER MOn 3 


EN 


672 


RBV PWR 


OFF 


731 


CCC 


OFF 


432 


CAM 1 


OFF 


511 


CAM 2 


OFF 


510 


CAM 3 


OFF 


512 



19-2 



RBV SUBSYSTEM 



SO 



L 



CS I 



CS 2 



CE 1 



3 



CE 2 



[CS3 




CE 3 















ccc 



o 

Q 



SPACECRAFT 



WBVTR 
A 



WBVTR 
B 



O 
H 



O 

o 



AUX 

VIDEO 



TRANSMITTER 



RF 

UNK 



CD 
CO 



FM 

RECEIVER 



P^ TAPES TRAhB PORTED TO NDPF FOR BULK AND SELECTEu PRECISION PROCESSING 



TR70 
VIDEO 
TAPE 
RECORDER 



ALTERNATE DC 
RESTORED VIDEO 




Figure 19-1. Return Beam Vidicon System Functional Block Diagram 



I 



o O 


**1 s* 


»-* 


>V O 


8^ 


5=^^ 


PAGE 
QUALr 



£3 




4^. 'fesM' i'^,f-^-«fi Nr:r.<^PJ^*^.5.lBii^^fJiS^^^"l 



£t^ 



Figure 19-2, Return Beain Vidicom 



Table 19-2. RBV Initial Tum-ON, Orbit 41, 25 January 1975 



Time 


Activity 


16:21:04 


WPA-1 ON 


16:23:12 


WBR-1 RECORD 


16:23:59 


CAM 1 ON 


16:24:00 


RBV ON 


16:25:51 


RBV OFF 




CAM 1 OFF 


16:26:23 


CAM 2 ON 




RBV ON 


16:27:59 


RBV OFF 




CAM 2 OFF 


16:28:31 


CAM 3 ON 




RBV ON 


16:30:23 


RBV OFF 




CAM 3 OFF 


16:30:56 


CAM 1 ON 




CAM 2 ON 




CAM 3 ON 




RBV ON 


16:34:01 


WBR-1 OFF 


16:34:07 


RBV OFF 




WPA-1 OFF 



19-5 



Table 19-3. RBV Telemetry Values 







Telemetry Values 


T.V. 


Orbit 


Ftme. No. 


Name 


Norm 


41 


14001 


CCC Board Temp (DGC) 




19. 939 


14002 


CCC PWR Sup. Temp (DGC) 




21. 047 


14003 


15V SUPPLY (TMV) 




3.950 


14004 


+6V, -5. 25 PWR, SUP (TMV) 




3.075 


14100) 




0.96 




142 00> 


VIDEO OUTPUT VOLT (TMV) 


0.93 




14300) 




1.06 




14102] 




3. 75 to 4. 02 


3.950 


14202 [ 


COMBINED ALIGNMENT CUR (TMV) 


3. 87 to 4. 10 


3.875 


14302 ) 




3. 80 to 4. 05 


3.850 


14103) 






24. 363 


14203 > 


TEMP. IN ELEC. UNIT (DGC) 




20. 387 


14303 ) 






25.363 


14104] 






23. 363 


14204 i 


TEMP IN LV: PWR SUP PGC) 




18.834 


143041 






26. 023 


14105) 




3. 92 to 4. 07 


3.950 


14205> 


DEFL PWR SUP +10 (TMV) 




3.950 


14305) 






4.000 


14106| 




3. 65 to 3. 80 


3.700 


14206> 


L. V. PWR. Sup. +6 , -6. 3 (TMV) 




3.650 


14306) 






3.725 


14107) 




2.53 


2,650 


14207 > 


Current in Ther. Elec (TMV) 




2,500 


14307) 






2,575 


14108] 




1. 80 to 3. 50 


2.550 


14208 


Vidicon Fill. Cur. (TMV) 




2.400 


14308 ) 






2.575 


14111] 




3.03 


3.025 


14211 > 


Target Volt, to Vidicon (TMV) 




3.050 


14311 ) 






3.225 


14120] 




4.05 


4.050 


14220 [ 


Vert. Defl. Volt. (TMV) 




4.275 


14320) 






4.275 


14114) 




21.99 


21. 997 


142141 


Temp Vidicon Face Plate (DGC) 




21. 059 


14314) 






22. 398 


14115) 




24.17 


20. 940 


14215} 


Temp Focus Coil (DGC) 




20. 387 


14315 






21.940 



19-6 



Table 19-4. Return Beam Vidicon Subsystem 



• COMPONENTS 



CAMERA CONTROLLER COMBINER S/N 003 

CAMERA ELECTRONICS 1 (BLUE) S/N 003 

CAMERA ELECTRONICS 2 {YELLOW) S/N OOK 

(REPLACED ON 8/19/74 WITH) S/N 004 

CAMERA ELECTRONICS 3 (RED) S/N 008 

CAMERA SENSOR 1 (BLUE) S/N 003 

CAMERA SENSOR 2 (YELI-OW) S/N 002 

(REPLACED ON 8/19/74 WITH) S/N 004 

CAMERA SENSOR 3 (RED) S/N 008 

RBV MAGNET MOMENT ASSEMBL Y S/N 40513 

PKE-LAUNCH PERFORMANCE 
ALL EVALUATION PARAMETERS ARE SATESFACTORY. 



PRE-LAUNCH [PERFORMANCE SUMMARY 



SIGNAL/ NOISE 
(A. C, OUT) 

RADIANCE OUTPUT 

A) REPEATABILITY OF 
INTERNAL CALIBRA- 
TION LEVELS 

CAL 
CALl 
CAL 2 

B) WIJITE SHAD[NG-% 
(CENTER) 

RASTER S[ZE 

HORIZONTAL % 
VERTICAL % 

VERTICAL RESOLUTION 
(CENT. 59 LP) % 

HORIZONTAL RESOLUTION 
(CENT, 59 LP) % 



iSI>EC\ 



YELLOW 



REPEAT ABILfTY WITHIN 
50 MV (CAMERA TEMPER- 
ATURE A CONSTANT) 
15 I 15 [in 



REPEATABILITY 



REPEATABILrTY 



REPEATABILITY 



(RCA) 



.270 
.4S0 
.933 



100. 08 
100.28 



37, 3DB 



,244 
.566 
1.086 
19,1 



100. 00 
100, 16 



.343 
. 441 
, 869 
15.3 



100. 26 
100. 78 



fgfil 



YELLOW 



26 



.27 4 
,462 
.936 
17.4 



100. 04 
100.24 



.238 
.580 
1.0S2 
11,0 



100, 14 
100.26 



.330 
.439 
.864 
13.5 



100.56 
100.76 



PROBLEM 

• HORIZONTAL CENTERING SHIFT 

RED CAMERA - 6 TIMES AT GE 
(5/20/74 AND DURING AUGUST 
AND SEPT. 1974, EBPR 302, 
MR D08197, ) 

- BLUE CAMERA - ONCE AT RCA 

- YELLOW CAMKRA, S/N 004. 3 TIMES 
AT RCA 

YELLOW CAMERA, S/N 002, SHIFT 
NEVER OBSERVED. 

« LOSS OF VIDEO FROM BLUE AND YELLOW 
CAMERAS DURING THERMAL VACUUM TEST. 

HIGH VOLTAGE TRANSFORMER FAIL El) IN 
BOTH CAMERAS, (6/1/74 AND 6/5/74, 
EBPR 310, MR D08200 AND EBPR 342, 
MR D08190, ) 

« CAL 2 LEVEL OF YELLOW CAMERA IS 

SATURATED AND THEREFORE UNUSEABLE 
(B/21/74, EBPR 404. MR 0B266). 

• VERTICAL PORTION OF RE BEAU MARKS 
MISSING ON CAL 2 OF YELLOW CAMERA. 
(9/5/74, EBPR 446). 

• HORIZONTAL JITTER IN RED CAMERA 
ANCHOR MARK; ANCHOR MARK ALSO NOT 
VERTICAL, (9/6/74, EBPR 461). 



MULTILINE JUMP DUUNG YELLOW CAMERA 
OPERATION (9/7/74, EBPR 466). 



RESOLUTION 

UNABLE TO ISOLATE PROBLEM THROUGH 
EXTENSIVE TESTING AT RCA AND GE 
SHIFT OBSERVED IK ^^ 1^ OF DATA. 
SHIFT HAS NOT OCCURRED SINCE T/V 
ORBIT D- 10, 9/7/74, ACCEPT AS IS. 



HIGH VOLTAGE TRANSFORMER REDESIGNED. 
TRANSFORMERS REPLACED IN ALL CAMERAS. 



ACCEPT AS IS, USE CAL 1 LEVEL FOR 
INFLIGHT CALIBRATION CHECK. 



CAUSED BY AMPLIFIER SATURATION. 
CAMERA PERFORMANCE IS NOT DEGRADED. 
ACCEPT AS IS, 

SUSPECT JITTER RELATED TO HORIZONTAL 
PROBLEMS. 

ANCHOR MARK WAS NOT ETCHED VERTICALLY 
ON TUHK, ACCEPT AS IS, 

ONE TIME ONLY OCCURRENCE, 
ACCEPT AS IS. 



OKIQINAL PAGE IS 
OF POOR QUALITY 



19-7/8 



SECTION 20 
MULTISPECTRAL SCANNER SUBSYSTEM 



SECTION 20 
MULTISPECTRAL SCANNER SUBSYSTEM 

The Multispectral Scanner (MSS) system consists of spacecraft and ground equipment which 
permits images of the earth to be obtained simultaneously in 4 or 5 spectral bands* The 
LANDSAT-2 MSS uses a 4-band scanner operating in the solar reflected spectral region 
from 0. 5 to 1, 1 micrometers (microns) wave length, and scans cross track swatchs of 
0. 5 km width (at a 496-nm altitude), imaging six scan lines across in each of the four 
spectral bands simultaneously. The object plane is scanned by means of an oscillating 
flat mirror between the scene and the double reflector telescope optical chain. The 11.56 
degree cross-track field-of-view is scanned as the mirror oscillates approximately +2.89 
degrees 13. 62 times per second about its nominal position as shown in Figure 20-1 • 

The instantaneous field-of-view of each detector subtends an earth -area square of 256 feet 
on a side from the nominal orbit altitude. Field stops are formed for each line imaged 
during a scan, and for each spectral baud, by the square input end of an optical fiber. Six 
of these fibers in each of four bands are arranged In a 4 x 6 matrix in the focal plane of 
the telescope. See Figure 20-2 for functional block diagram, and Figure 20-3 for pictorial 
view. An equipment list is shown in Appendix A. 

The Multispectral Scanner (MSS) was launched in the OFF mode, except that the Rotating 
Shutter was commanded ON to distribute the launch mode stresses around the bearing. 
The complete launch configuration is shown in Table 20-1. Verification of this configura- 
tion was obtained from telemetry in Orbit 1 at Madrid, and by playback from Orbit 1 at 
Alaska. 

In Orbit 1 at Alaska, the rotating shutter (and the enabling primary power switch for MSS) 
was commanded OFF at 19:29:45. 



20^1 




/OSCILLATING 
SCAN MIRROR 



6 DETECTORS 
PER BAND 
(24 TOTAL) 



NORTH 




/ \ / -/ ^ LINES/SCAN/BAND 



WEST 



EAST 



SOUTH 




ACTIVE SCAN 
' DIRECTION 



PATH OF SPACECRAFT 
TRAVEL 



Figure 20-1. MSS Scanning Arrangement 



20-2 



OBIGINAL PAGE IS 
'W POOR QUALITY 




WIDE BAND VIDEO 
TAPE RECORDER 



WIDE BAND 
MODULATOR 



STATUS 

MONITOR 



RSE TEST 
SET 



1 



DEMUX 




FRM928 

TAPE 

RECORDER 




Figure 20-2. Simplified Functions Block Diagram of the 
Overall MSS System 



20-3 



fed 

t 



St 

o 



I > 
63 







Figure 20-3. Multispectral Scanner 



Table 20-1. Multispectral Scanner Subsystem Laxuich Mode 



Mode 



Cmd 



MSS BOTH 
SYSTEM PWR 
HIGH VOLT 
SELINV 
BAND 1 
BAND 2 
BANDS 
BAND 1 HV 
BAND 2 HV 
BAND 3 HV 
BAND 1 HV 
BAND 2 HV 
BAND 3 HV 
SHUTTER 
ROT SHUTTER 
CAL LAMP 
CAL LAMP 
SCAN PWR 
SCAN MON 
SCAN MON 
SCAN MIRROR 
SCAN MIR PWR 
MIR SCAN 
MUX 

MUX MODE 
HEATER 
SYS ON/OFF 
BAND 1 GAIN 
BAND 2 GAIN 



EN 

ON 

OFF 

A 

OFF 

OFF 

OFF 

A 

A 

A 

OFF 

OFF 

OFF 

A 

ON 

A 

OFF 

1 

OFF 

A 

INH 

1 

OFF 

INH 

COMP 

OFF 

NORM 

LO 

LO 



632 

052 

073 

053 

076 

132 

135 

054 

055 

056 

176 

233 

232 

214 

152 

117 

177 

217 

172 

255 

256 

312 

335 

276 

315 

735 

316 

175 

174 



INITIAL TURN-ON 

The initial tiim-on of the MSS subsystem was in Orbit 19 during a Merritt Island/Green- 
belt/Alaska pass. The commands and execution times are shown in Table 20-2, 

The WBPA-2 was tvimed on by stored command at 02:00:16. 

Telemetry values , video and strip charts were normal. 



20-5 



Table 20-2. MSS Initial Turn-On Orbit 19, 24 January 1975 



Cmd 


Activity 


Time 


H 


M 


S. 


VIA MERRITT ISLAND 










775 


USB ON 


01 


57 


14 


316 


MSS ON NORM 


01 


59 


57 


316 


MSS ON NORM 


02 


01 


29 


650 


WBR-2 ON 


02 


01 


59 


572 


WBR-2 STBY 


02 


02 


03 


513 


WBR-2 REG 


02 


02 


16 


156 


CAL LAMP ON 


02 


02 


24 


153 


SCAN MON ON 


02 


02 


34 


277 


SCAN MIR NORM 


02 


02 


44 


314 


MID SCAN CODE ON 


02 


02 


55 


610 


MSS ENABLE 


02 


03 


05 


257 


MUX NORM 


02 


07 


26 


052 


MSS SYS ON 


02 


07 


33 


212 


BN 2 HV ON 


02 


07 


51 


233 


BN 2 HV OFF 


02 


08 


04 


132 


BN 2 OFF 


02 


08 


17 


114 


BN3 ON 


02 


08 


45 


112 


MSS HV ON 


02 


08 


58 


213 


BN 3 HV ON 


02 


09 


09 


VIA GREENBELT 










057 


BNl ON 


02 


10 


26 


157 


BN 1 HV ON 


02 


10 


40 


113 


BN2 0N 


02 


10 


48 


212 


BN 2 HV ON 


02 


10 


57 


VIA ALASKA 










073 


MSS SYS OFF 


02 


14 


47 


766 


PYLDS OFF 


02 


15 


10 


067 


WBPA-2 OFF 


02 


15 


23 


757 


USB OFF 


02 


22 


54 



20-6 



SUBSEQUENT OPERATIONS 

In Orbit 21 a sun calibration was performed while over Alaska. Configuration was prime, 
compressed, low, with mid-scan code ON. The results as reported by Alaska are shown 
in Table 20-3. 

Table 20-3. MSS Sun Calibration in Orbit 21 Reported by ALASKA 



START TIME OF SUN CAL PULSE 


05:47:02 


DELAY TIME FROM LINE ST. <MS) 


18 


PEAK AMPLITUDE 


SENSOR 


VOLTS 
(on 4V FULL SCALE) 


1 
2 
5 




3.0 
3.1 
3.1 


7 




3.6 


8 
12 
13 
15 




3.5 
3.3 

3.0 
3.2 


18 




3.2 


19 




2.2 


20 
23 




2.1 

2.2 



The MSS was also operated in Orbits 27, 28 and 42 in realtime operations; and in Orbit 
40 to Record on WBR-1. A second sun calibration was made in Orbit 47 with results 
similar to those of Orbit 21* 

Typical telemetry values are shown in Table 20-4. Table 20-5 shows the pre-launch per^ 
form an ce of the MSS. 



In Appendix E the same MSS scene is shown in 5 successive figures, F-1 thru F-5, one 
for each of the four bands ^ and the final one a composite of 3 bands 



20-7 



Table 20-4. MSS Telemetry 



Function 



15040 
15041 
42 
43 
44 
45 
46 
47 
48 
49 
15150 
51 
52 
53 
54 
55 
56 
57 
58 
59 
15060 
61 
62 
63 
64 
65 
66 
67 
68 
69 
15070 
15071 



Name 



MUX -6 VDC (TMV) 

A/D SUPPLY (TMV) 

AVERAGE DENSITY <TMV) 

FIBER OPTICS PLATE 1 TEMP (DGC) 

FIBER OPTICS PLATE 2 TEMP (DGC) 

MUX TEMP (DGC) 

ELEC COVER TEMP (DGC) 

PWR. SUP. TEMP. (DGC) 

SCAN MIR REG. TEMP (DGC) 

SCAN MIR DRIVE ELEC. TEMP. (DGC) 

SCAN MIR DRIVE COVER TEMP (DGC) 

SCAN MIR TEMP (DGC) 

ROT. SHUT HOUSING TEMP (DGC) 

SCAN MIR REG VOLT (TMV) 

CAL LAMP CURRENT (TMV) 

BAND 1 15 VDC (TMV) 

BAND 2 15 VDC (TMV) 

BAND 3 15 VDC (TMV) 

BAND 4 15 VDC (TMV) 

TLM 15 VDC (TMV) 

+12 VDC +6 VDC (TMV) 

LOGIC +5 VDC (TMV) 

RECT. +19 VDC (TMV) 

RECT. -19 VDC (TMV) 

BAND 1 HVA (TMV) 

BAND 1 HVB (TMV) 

BAND 2 HVA (TMV) 

BAND 2 HVB (TMV) 

BAND 3 HVA (TMV) 

BAND 3 HVB (TMV) 

SHUT MOT. CONTR. INTEG (TMV) 

SCAN MIRROR DRIVE CLOCK (TMV) 



* 

T.V. 
Norm 



Orbits 



27 



3.92 


4.05 


5.74 


5.95 


1.72 


1.71 


22.30 


18.13 


22.30 


17.87 


25.59 


23.38 


23.09 


20.25 


23.85 


19.45 


23.44 


18.30 


24.34 


18.96 


22.50 


17.26 


21.87 


17.26 


22.58 


23.26 


4.56 


4.7 


1.18 


1.17 


4.97 


4.98 


5.00 


5.00 


4.88 


4.95 


4.83 


5.00 


5.04 


5.06 


4.92 


5.03 


4.86 


4.81 


4.97 


5.03 


3.54 


3.60 


4.95 


4.95 


5.03 


OFF 


4.72 


4.70 


4.70 


OFF 


4.75 


4.72 


4.65 


OFF 


2.49 


2.60 


1.93 


2.00 



♦Thermal Vacuum Test Data at 2o'^C. 



20-8 



Table 20-5. Multispectral Scanner 



COMPONENT SUMMARY 

• SCANNER S/N-2 

• MUX S/N-1 

• LINE FILTER S/N-4 

PRE -LAUNCH PERFORMANCE SUMMARY 
PARAMETER 



SPEC 



PRE-LAUNCH 

MEASUREMENT 



• SIGNAL/NOBE 



• HORIZONTAL MTF 

• CROSS AXIS JITTER 

• SCAN SYMMETRY 

• LINE LENGTH VARIATION 



Bl 90 

B2 69 

B3 45 

B4 104 



> OO70 

(SWR) 
+ 30 /iRAD 



+ 2 WORDS 
LINE TO 
LINE 



MEAN 
MEAN 
MEAN 
MEAN 



LIN 

109.6 
96.6 
72.9 

133.0 



COMP 

108.8 
82.5 
66.6 



WORST CASE SI, CL 80.2 
WORST CASE SIO, CL 69. 1 
WORST CASE S14, CL 59.4 
WORST CASE S20, LL 108. 



ALL CHANNELS > 3 9% 



MEAN = 1. 1 ^RAD MAX = 5. 2 /jRAD 

0.4990 (NO. WORDS TO MSC/TOTAL LINE LENGTH) 

MAX + 2 WORDS OVER 35 MINUTES 
9 WORDS OVER IS^C CHANGE 
MEAN = 3247 @ 23^0 



o 



CO 



to 

o 
1 



Table 20-5. Multispectral Scanner (Cont'd) 



PARAMETER 
VIDEO STABILITY 



SPEC 



PRE-LAUNCH MEASUREMENT 

2% VARIATION OVER 17 MINUTES AFTER 3 MINUTE 
WARMUP. 



GAIN (22 C, COMP LO) 
(QL/MW CM-2 STEAR. ~^ 
(VACUUM) 



OFFSET (22 C, COMP LO) 
QUANTUM LEVEL (FULL 
RANGE - 64 QL'S) 



NOMINAL 




MEAN 


MAX 


(SEN) 


MIN 


(SEN) 


Bl 25.80 


Bl 


26.14 


26.97 


(6) 


25.07 


(1) 


B2 32.00 


B2 


34.39 


35.91 


(10) 


32.64 


(12) 


B3 36.36 


B3 


38.45 


39.96 


(18) 


36.10 


(13) 


B4 13. 91 


B4 


13,10 


13.34 


(24) 


12.62 


(22) 


>0 


Bl 


+1.00 


+1.38 


(5) 


+0.73 


(3) 


<0.8 


B2 


+0.79 


+1.03 


(12) 


+0.52 


(7) 


(LINEAR MODE 


B3 


+0.75 


+1-01 


(17) 


+0.35 


(14) 


IN SPEC.) 


B4 


+0.82 


+1.28 


(23) 


+0.43 


(22) 



TEMP. SENSITIVITY 
(10 TO 35°C) 



% GAIN CHANGE/'c 



Bl 


-0. 21% 


-0.32% (1) 


B2 


-0. 35% 


-0.39% (8) 


B3 


-0.43% 


-0, 49% (18) 


B4 


+0.30% 


+0. 35% (21) 



-0. 06% (4) 
-0.22% (10) 
-0.22% (13) 
+0. 029% (23) 



Table 20-5. Multispectral Sensor (Cont'd) 



PARAMETER 

TEMP REPEATABILITY 
(lO^C TO 35<^C) 



SPEC 



PRE -LAUNCH MEASUREMENT 
ALL BANDS + 2.0% 



CAL WEDGE CORRECTION 
WITH TEMP. (IQOC TO SS^C) 
% CHANGE /OC 
(MEAN VALUES) 



VIDEO SENSITIVITY TO HOVK 
SPHERE TARGET (NORMALIZED 
TO FULL SCALE) % GAIN CHANGE 
OVER A ZERO RADIANCE INPUT 
COMPUTED FROM CAL WEDGE 





LAMP A 




LAMPB 




UNCOR 


COR 


UNCOR COR 


Bl 


-.286 


-.098 


-.254 -.038 


B2 


-.405 


-.062 


-.370 -.052 


B3 


-.469 


-.054 


-.459 -.027 


B4 


+.399 


+.111 


+. 366 +. 082 




MEAN 




WORST CASE 


Bl 


+4.3% 




S3, +6% 


B2 


+4.2% 




S8, +6% 


B3 


+2.8% 




SI 8, +5% 


B4 


-0. 1% 




S24, +0.5% 



to 
o 

1 



to 

o 



tS3 



Table 20-5. Multispectral Sensor (Cont'd) 
PRE-LAUNCH MSS RADIOMETRIC CALIBRATION 



THREE CALIBRATIONS 

• POST INTEGRATION (5/74) 

• POST TV n (9/74) 

• POST VIBRATION (10/74) 



POST INTEGRATION 



REPEATABILITY 
(CORRECTED) 

REPEATABILITY 
(CORRECTED) 



POST TV 11 



BANDS 1-3 -0.8 + 0.6% 
BAND 4 +0.2+0.5% 

BANDS 1-3 +3. 3 + 1%* 
BAND 4 -3.4 + 0.5% 



POST VIBRATION 
BANDS 1-3 -1. 5 + 0. 8% 
BAND 4 -1.0+0.4% 

BANDS 1-3 -1. 4 + 0. 8%* 
BAND 4 -2.6+0.5% 



♦SENSOR 8 = +6. 2%, +3. 7% 
SENSOR 10 = +6. 8%, +4. 2% 



Table 20-5. Multispectral Sensor (Cont'd) 



PRE-IAUNCH PROBLEM SUMMARY 



V/TI 



V/TI 



V/T 



POST VIB 



PROBLEM 

• VIDEO (0. 5 MSEC) OCCURS PRO- 
CEEDING PREAMBLE, CAUSES 
DEMUX TO MBS LINE 

START OR FIND FALSE LINE 
START. EBPR 306. 

• SCAN MONITOR A AND B OUT OF 
ALIGNMENT BELOW 20<^C. EBPR 293, 
MR D08191, MR D08199. 

• APPARENT GAIN CHANGE IN CAL 
WEDGE FROM AMBIENT TO VACUUM. 

Bl - 13% 
B2 - 3% 
B3 - 7% 
B4 + 11% 

• SUN CAL MIRROR ALIGNMENT OFF 
2° IN AZIMUTH FROM HAC DATA. 
EBPR 535, D07204. 



RESOLUTION 

REPHASE SHUTTER SUCH THAT SHUTTER 
OPENS DURING PREAMBLE. PROBLEM 
DID NOT APPEAR m V/T H. 



RE -ALIGN SCAN MONITORS, PROBLEM 
DID NOT APPEAR IN V/T H. 



PROBLEM REPEATABLE, WAS OBSERVED 
AT HAC, EXTERNAL TARGET REMAINED 
CONSTANT. CALIBRATION IS STABLE 
AND REPEATABLE IN VACUUM. ACCEPT 
AS IS. 



ACCEPT AS IS. INSPECTION REVEALED 
THAT MIRROR WAS FIRMLY IN PLACE. 
NO APPARENT MOVEMENT. 



to 
o 
I 



SECTION 21 
DATA COLLECTION SUBSYSTEM (DCS) 



SECTION 21 
DATA COLLECTION SUBSYSTEM (DCS) 

The Data Collection System is designed to relay data from randomly distributed Data Col- 
lection Platforms (DCP) through the LANDSAT-2 spacecraft to either receiving sites, Green- 
belt, Md. or Golds tone, Calif. The DCS system is designed to collect and provide at least 
one message from each of up to 1000 Data Collection Platforms in the continental United 
States every 12 hours, with a probability of 0* 95, with a nominal LANDSAT S/C orbit and 
both ground stations operating. See Figure 21-1 for system description, Figure 21-2 for 
ftinctional block diagram, and Figure 21-3 for pictorial view. See Appendix A for hardware 
listing. 

The Data Collection System was launched in the mode shown in Table 21-1, Verification of 
this mode was obtained by CRT displays and strip charts from telemetry received from 
Madrid and playback from Alaska early in Orbit 1. About 100 DCS ground station platforms 
were operatioaial at launch time. 



Table 21-1. Data Collection System Launch 
Mode 



INITIAL- TURN-ON 
DCS Receiver No. 1 was turned ON at 
02:02:08 in Orbit 5, and has been left ON 
since. The equipment operated normally. 
Telemetry values are shown in Table 21-2. 
In Orbit 6, the first complete orbit after turn-on, 348 messages were received, most of 
them simultaneously at Greenbelt and Goldstone, 



Receiver 1 
Receiver 2 


Mode 


CMD 


OFF 
OFF 


407 
406 



SUBSEQUENT OPERATIONS 
Overall performance of the Data Collection System during the remaining orbits has been well 
within the system design. PIR-U-1N23-ERTS-130 in Appendix F demonstrates that effective- 
ness of the DCS with LANDSAT-2 is at least as high as that with LANDSAT- 1. An average of 
over 5 messages are being received from each platform each 12 hours. 



21-1 



Table 21-2. DCS Telemetry Values 



FllBC. 




* 
20<'C 


Orbits 














No. 


Name 


Plateau 


5 


15 


25 


36 


49 


16001 


Receiver 1 Sig Strength (DBM)** 


-199 


-123.34 


-122.71 


-123. 40 


-121.66 


-124, 35 


16002 


Receiver 1 Temp (DGC) 


23.4 


22.54 


24.02 


24.42 


24.40 


24.45 


16003 


Rec-1 Pwr Siput Volt (VDC) 


2.37 


2.35 


2.37 


2,37 


2.37 


2.37 


16004 


Receiver 2 Sig Volt (DBM) 


-119 


F 


F 


F 


F 


F 


16005 


Receiver 2 Temp (DGC) 


22.3 


F 


F 


F 


F 


F 


16006 


Receiver 2 Input Volt (VDC) 


2,35 


F 


F 


F 


F 


F 



♦Thermal Vacuum Test Data 
**This value is for a CW carrier only; it is not valid during DCS message reception. 
F=Receiver 2 was OFF 



Table 21-3 describes pre-launch subsystem performance. 



Table 21-3. DCS Subsystem 



• Component 

Receiver A S/N EAB-FT-2 

Receiver B S/N EAB-FT-3 

• Pre- Launch Performance 



DCS 

Performance 



Level 



Receiver No, 1 Receiver No. 2 



Dynamic Range -70 to -121 DBM 2. PP 

input signal strength 

Translation F up -F down 400. 525 MHz 

Frequency 



2.0 PP 



Spec 
2.0 + 0.2 PP 



Miss Rate 
Error Rate 



-119 DBM 
-119 DBM 



0. 7 X 10 



<10^ 



400. 524 MHz 400. 526 + , 006 MHz 



-2 2 

1, 3 X 10 < 5 X 10' 



<10 



-5 



@ -117 DBM 

<10~^ 
@-117 DBM 



• Pre- Launch Problem Summary 

No problems throughout environmental test program. 



21-2 







to 



I 

00 



Figure 21-1, LANr)SAT-2 Data Collection System 



to 

I 
4^ 



COAX 
SWITCH 



S/fc DCS 
RECEIVER t 



401.55 MHz 
UPLIM< 




St; DCS 
RECEIVER 2 



COAX 
SWITCH 




8 ANALOG OR 
DIGITAL SENSOR INPUTS 



—I- 0-- 



MODULATION 

AND 

TRANSMISSION 



A/b 

CONVERSION 
AND 

MULTIPLEXINra 



ERROR 
CONTROL 
ENCODING 



1 



MESSAGE 
FORMATTING 




1.02 MH^ *R 



i/j 



US BE TLM 

EQUIPMENT 

(REDUNDANT) 




2287.5 MHz 

USB 

DOWNLINK 




r " 
I 

I REMOTE 
» SITE 
iGOLDSTONE 
I CALIF. 

* ..— -J 



\ DATA COLLECTION^LATFORM (DCP) I 




NASCOM 



LISTING CATALOG 
AND CARDS 
V _^ 



TELETYPE 
NETWORK ! 



USB 
RECEIVER 



\f 



REMOTE 
SITE 
NTTE 
GODDARD 



H 1.024 MHz S/t 
I FM DEMQD ] 

7 

1 BIT DEMQD I 
1 



DECODER 



FORMATTER 

AND 

BUFFER 



DCS/^SE 



SYSTEM OUTPUTS 



Figure 21-2, Data Collection Data Flow 



KSKKEIVEI 



O O 

to 




bo 



I 
en 



a> 



Figure 21-3. Data Collection Subsystem 



APPENDIX A 
LANDSAT-2 CONFIGURATION 



-X 



I/I VHP COmmAkQ 



4/4 POWfRCjOlffe' 
TOP A^.D C")2'*^^ 



\ 0/4 BAJX 
4/4 aocK 









TOP AAJD C^O-rrCtf^ 



4/0 fl-^rrc-^v y-TOr* AfCA/- /K*SuL' 




ASSYS (I6PLACES ^S 



dCTrc*f ACVyAS-i 



^jb PCM m/^o^iA c -fl BA-rrfirv\ 

SECTion A" A 






5.4" 



ORIGINAL PAGE JS 
Of P0QE QUALHY 



1 








-*/4 


— 




^/4 


— 


^/4. 


_„ 




^U 


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V4. 






^/4 1 







♦/* 






4v4 





r4/5 


\^/t 




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-»/^ 


— 




*/^ 


" 




*/j 







i/4 


'/o 




V4. 




4/* 


— 




4^4 1 


^t::.. . 



Figure A-i, LANDSAT-2 Equipment and Payload Location 



A-1 



> 

I 
to 






POiMFH S£a 
BAY n 

000^ 






ISM 




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BAY tS 



BATTERf 

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73 



mmo aoac 

BAY S 
¥7£2/3/Qr^3 



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Figure A-2. LANDSAT-2 Equipment and Payload Location 



♦ K- 



OS 

o ^ 

is 



^ii?^r:^t^ f^gy^ j;;^ ^^/^ BATTERS 

S/^ 039 



BATTBI^Y 
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Figure A-3. LANDSAT-2 Equipment and Pay load Location 






mEifomitcs^ 



n>/> W£i¥ 



y/^/f 



*i'rt>zzH3^QZ 



RBCOHDER'' 







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Figure A -4. LANDSAT-2 Equipment and Pay load Location 



oo 


►^ tti 


1— ( 


^o 


^g 


w> 


t^ 


r* 2 


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Figure A-5. LANDSAT-2 Equipment and Payload Location 



I 




PADDLES DEPLOrED 



Figure A -6. LANDS AT -2 Equipment 




n 



< -T - ^ 



AUX. LOAD 



\ WIDE E£.MI> 



+ X CR6IT ADJUST 9!^l7-.'i^ 
THRUSTER^KtA'i) ClA^.: "" 



(ECAM)- 




EMVELOKr 
SOLAR ar;^a/ 

OKuTTcD POR 
CLARlTV 






^Paddle la'^ch ^^^ 

MECHAMiSM 



USB ANTENNA 
MOUNT 



USB Ar^TEKiNA -^ *r \ f 

WB ANTENKA— . 



■RBV 



-UHF ANTENNA MOUNT 



-UHF DCS ANTENNA 






AXIS X'X PROFILE 



ORIGINAL PAGE IS 
OF POOR QUALITY 



Figure A-7. LANDSAT-2 Configuration 



A-7 



WIDE BAMD -, 

RECORDER. 

£LECTR0i^iCS*2 




VHF COf^MAHD A^a^i.^^.A 

STATlOn 107 



UPPER. GROUISD 
PLANE 



^ SOLAR ARRAY «M 
STOWED POSaiON 



ATTITUDE COhTROL 
SUB SYSTEM (ACS) 

-ALBEDO SHIELD 

-Ace/SOLAR PADDLE SUPPORT \j? 

STA.lSb -e SOLAR PADDLE SHAFT 

-HORlZCh SCAINMER 

PADDLE T RAN SiTiCh SKTIOH 

LOV^ER GROUMD 
PLAriE 



RADDLE FOLD 
H)riGE LPNE 



'WIDE BAND RECORDER 
ELECT ROM ICS** 



*X OREIT ADJUST 
TNRUSTER 



SEflSORY RING 



I 



irSSULATOM 
(TOP 4 BOTTOM 

•STATION ao8 



.1 



-SEPARATIOH BAND 
-STATiOti EEl 






SEPARATCN Plane 

ADAPTER 



_AXiS y-V PROFILE 




STATtOhi 2A5 



MULTl SPECTRAL 
5CAMNER 



A-8 



Figure A^S. LANDSAT^2 Configuration 






moim:7mwm 





^N 


/// 




%fi /4w (s^C£^AS r/*T^) 






am^LO^Bm 






¥7£ZfZ7fS^Pf 






sfit rr-f 


ss 






^ w 






»— 1 






*Ti O 






INAL 
OOR 






PAGE is 
QUALITY 




-V 



^t^tiirupi 



mEM[il^.FK^ B 



i7£2n7ffP^ 

s/^ firm 







wu^mAym^i^) 






mM£^FI^. W 



Sffid FTCZ 



^WS/SF 



^ firs 



^£ZtJ70$ Pt *7r VOttP 6S 



> 



Figure A-9, LANDS AT-2 Attitude Control System 




ffefe 



Figure A-lO. LANDSAT-2 Observatory Reference Axes 



A-io 



A^ 



^^^•'^^ 



^nt"^ 



CONSOLIDATED CONFIGURED ARTICLES LIST 



ERTS SPACECRAFT 90 3 



(LANDSAT 2) 



Revision Status of Pages 



SHEET # 



I (INDEX) 
2 
3 
4 

5 
6 
7 
8 

9 
10 
11 
12 

13 
14 
15 
16 

17 
18 
19 
20 



INITIAli 
ISSUE 



4/12/74 
4/12/74 
4/12/74 
4/12/74 

4/12/74 
A/12/74 
4/12/74 
4/12/74 

4/12/74 
4/12/74 

4/12/74 
4/12/74 

A/12/74 
4/12/74 
4/12/74 
4/12/74 

4/12/74 
4/12/74 
4/12/74 
4/12/74 



REV 
A 



11/6/74 

11/6/74 
5/20/74 



11/6/74 



11/6/74 



REV 
B 



5/20/74 
11/6/74 



12/16/74 
12/16/74 



REV 
C 



REV 
D 



REV 
E 



REV 
F 



REV 
G 



Note 1. Those items which have been added or changed in this revision are noted 
with heavy black lines in the right margin. 

2. Change-out lop since January 1, 1973 appears on back of cover sheet. 



ISSUED BY CONFIGURATION MANAGEMENT OFFICE 

December 16, 1974 



A-11 



> 

I 

INS 



CONFIGURATION CHANGES SINCE JANUARY 1, 1973 




NOMENCLATURE 



Batteries 

PCM TLM Recorder #1 

MSS Multiplexer 

Power Control Module 

US BE 

Batteries 

Batteries 



MSS Scanner 
WB Frequency Hoc!. 
Med u 1 a t o r 
WBFM Power Supply 
MSS Multiplexer 
MSS Scanner 
RBV MMCA 
RBV CCC 
VIP >femory B 
D<^tterxes 

US3E 

APU 

WBVTR Elect. v2 

RBV Electronics ^2 

RBV CCC 

WBVTR Electronics ^2 
WBVTR Electronics -Tl 

RBV Camera i^2 

Comriand Clock 

WBVTR V2 

WBVTR in 

WBVTR Electronics ^1 

WBVTR #1 

Cotmnand Clock 

MSS Scanner 

MSS Scanner 

WBVTR ir'l 

WBVTR Electronics ^1 

RBV CCC 

ECAM 

WBVTR Electronics #1 



DRAWING NO. 



2265943-501 

202&35-001 

324LU0-100 

1759712-302 

0L'P09566C001 

2265943-501 

2265<)43-501 



43727 
47E221815G1 

47C223321G1 

3241140-110 

43727 

47D224600C1 

2265336-501 

6Q3191G10 

2265941-501 

JI-P09566C001 

47E221855G1 

S370323-501 

1976466-501 

2265336-501 

3370323-501 

S370323-501 

W76477-501 

20J01-102-301 

SJ5S497-501 

3358497-501 

S370323-501 

8358497-501 

20001-102-301 

43727 

43727 

8358497-501 

8370323-501 

2265336-501 

GF1308902 

8370323-501 



rJi MOVED 



DATE 



3/27/73 
3/27/73 
4/12/73 
5/10/73 
5/30/73 
7/24/73 

7/26/73 



11/9/73 
11/13/73 

11/29/73 

11/13/73 

12/26/73 

1/2/74 

1/7/74 

1/29/74, 

3/11/74 

3/13/74 
4/24/74 
5/10/74 
6/16/74 
6/1^^74 
6/16/74 
6/16/74 
6/17/74 
6/17/74 
6/21/74 
6/21/74 
7/17/74 
7/17/74 
7/21/74 
7/15/74 
7/25/74 
7/26/74 
7/26/74 
S/16/74 
8/16/74 
11/8/74 



S.N. 



049-056 

EAB-n3 

I 

010 

EAB-QM 

059, 062 

057, 058, 

060, 061, 
063, 064 

ENG 

6 549507 

6549510 
ENG 

2 

6549513 

003 

008 
ENG 008, 
009 
EAB-FTl 
6549504 
FLTl 

002 

003 
Fl-Tl 
FLT2 

0C2 
EAB-FT2 
FLTl 
FLT2 
FLT6 
FLT6 
F003 
2 
2 
FLTl 
FLTl 

002 

101 

FLT2 



REPLACED 



DATE 



3/27/73 

3727/73 

10/11/73 

5/25/73 

5/31/73 

10/8/73 

3/11/74 



12/3/73 
11/29/73 

11/29/73 

12/3/73 

4/4/74 

3/6/74 

1/18/74 

2/12/74 

3/11/74 

3/13/74 
4/24/74 
5/16/74 
8/19/74 
7/25/74 
7/15/74 
7/16/74 
8/19/74 
6/17/74 
7/15/74 
7/16/74 
7/23/74 
7/23/74 
7/22/74 
7/24/74 
7/29/74 
7/26/74 
7/26/74 
8/19/74 
8/20/74 
11/11/74 



S.N. 



057-064 
EAB-QMl 
ENG, 

010 
EAB-FTl 
ENG 008, 

009 
057, 058 
060, 061 
063, 064 

2 
6549505 

654950B 

1 

2 

6549513 

003 

008 

059, 062 

EAB-QM 

6549502 

FLTl 

004 

002 
FLT6 
FLT6 

004 
F003 
FLT6 
FLT6 
FLTl 
FLTl 
EAB-FT2 

2 

2 
FLT2 
FLT2 

003 

LOl 
FLT 2 



COrfMENTS 



Install Flight batteries 

Quel Unit has better test history 

Return to Hughes for rework 

Reworked 

Test Anomaly (DO3770) 

Flight ursits in cold storage 

Cold storage 



Install Flight Unit 
Install Flight Unit 

Install Flight Unit 
Reinstall after rework 
Removed for special test 



Memory was re programmed 
Reinstall Flight batteries 

Test anomaly (D07227) 
Test anomaly (D08157) 
Removed for rework 
Removed for rework 
Test anomaly (D03159) 
Trouble- shoot MR D08150 
Test anomaly (D08193) 
Removed for rework 
Test anomaly (D03i93) 
Trouble-shoot MR D0315C 
Test Anomaly (D08193) 
Trouble-shoot MR D08150 

Trouble-shoot I^ D08150 
Returned after rework 

Reworked 
Reworked 

Trouble -shoot MR D0815O 
Trouble -shoot MR D08150 
Returned after 'rework. 
Reworked 
Reworked 



CONSOLIDATED CONFIGURED ARTICLES LIST 
ERTS SPACECRAFT 903 





INDEX 




Item 


Page 


Item 


Page 


Adapter 


6 


Power Control Module 


9 


Antennas 


19 


Power Subsystem 


.9-10 


Attitude Control System 


16-19 


Power Supply, WBFM 


5 


Attitude Measurement Sensor 


13 


Power Switching Module (PSM) 


5 


Aux. Load Controller 


6 


Pref light Disconnect 


6 


Aux, Load Panels 


2 


Premodulation Processor 


6 


Aux. Processing Unit 


3 










Rate Measuring Package (EMP) 


18 


Batteries 


10 


Receiver , Command 


5 






Receivers, DCS 


6 


Clock, Command 


15 


Return Beam Vidicon MMCA 


5 


Command Integration Unit (CIU) 


2 


Roll Reaction Wheel Scan/Sig.Proc. 


16,17 


Command Receiver 


5 


Return Beam Vidicon (RBV) , & Electr. 


20 


Control Logic Box 


16 


S Band Equipment, Unified 


7,8 


Controller Aux. Load 


6 


Separation and Unfold Timer 


2 


Controllers Temperature 


4 


Separation Switches 


6 






Signal Processor, REWS 


16,17 


Dampers, Paddle 


19 


Solar Arrays 


9 


Data Collection System Receivers 


6 


Solar Array Drives (SAD) 


18 


Disconnect, Pref light 


6 


Storage Modules, Power 


10 






Structure. ACS 


16 


Filters, Wideband 


8 


Switches, Separation 


6 


Frequency Modulator, WB 


3 


Switch, Unfold 


2 


Initiation Timer 


17 


Tape Recorders, PCM TIM 


14 


Interface Switching Module 


15 


Telemetry Conversion Modules 


2 






Telemetry Conversion Modules, ACS 


16 


Mag. Moment Comp. Assembly- ACS 


13 


Temperature Controllers 


4 


Mag. Moment Comp. Assembly -REV 


5 


Thermal Subsystem, ACS 


16 


Module, Interface Switching 


15 


Timer, Initiation, ACS 


17 


Module. Fay load Regulator 


9 


Timer, Separation and Unfold 


2 


Module, Power Control 


9 ■ 


Transmitter, VHF 


20 


Module, Power Switching (PSM) 


5 






Module, Telemetry Conversion 


2 


Unfold Switch 


2 


Module, Telemetry Conversion, ACS 


16 


Unified S Band Equipment 


7,8 


Multi Spectral Scanner (MSS) , & Mux 


20 






Narrow Band Tape Recorder 


14 


Versatile Information Processor 


11,12 


Orbit Adjust Subsystem 


13 


Wideband Filter 


8 






Wideband Frequency Modulator (WBFM) 


3 


Paddle Dampers 


19 


WBFM Power Supply 


5 


Panels, Aux, Load 


2 


Wideband Power Amplifiers 


13,14 


Payload Regulator Module 


9 


Wideband Video Tape Recorder (WBVTR) 


20 


PCM TIW Tape Recorder 


14 


& Electr. 




Pitch Reaction Wheel 


16 






Pneumatics, ACS 


17 


Yaw Rate Gyro 


19 


Power Amplifiers, Wideband 


13,14 


Yaw Reaction Wheel 


J 



OHIGINAL PAGE IS 
2? Nm QUALITYf 



Page 1 
Rev. A 



A-13 



CONSOLIDATED CONFIGURED ARTICLES LIST 



ERTS SPACECRAFT 903 



NOMKHC1.ATUR E 




Dwo * i»Ai(r MoJ asv 


• intAt. HO. 


COMMAND INTEGRATION UNIT 


GE-SS 


47E221775G1 


AN -5 


6549449 


Chassis Ass'y Al 


GE-SS 


47D221813G1 


AN -3 


PQ516 


Cordwood Module A3 


GE-SS 


47D221797G1 


AN -4 


PQ245 


Cordwood Module A5 


GE-SS 


47D221798Gi 


AN -5 


PQ216 


Cordwood Module A6 


GE-SS 


47D221796G1 


AN -4 


PR401 


Cordwood Module A7 


GE-SS 


47D221799G1 


AN -4 


PP8B0 


Cordwood Module A8 


GE-SS 


47E221800G1 


AH -3 


PP883 


Stick Module A9 


GE-SS 


47E221801G1 


None 


PP694 


Stick Module A12 


GE-SS 


47E221804G1 


AN -1 


PP686 


Stick Module A13 


GE-SS 


47E221805G1 


None 


PP692 


Stick Module A14 


GE-SS 


47E221806Gi 


AN -2 


PP691 


Stick Module A15 


GE-SS 


47E221807G1 


AN -1 


PP688 


Cordwood Module A16 


GE-SS 


47E221852G1 


AN -2 


PP817 


Stick Module A17 


GE-SS 


47E221853G1 


AN -3 


PP835 


Cordwood Module A18 


GE-SS 


47E221851G1 


AN -5 


PP383 


Chassis Ass'y A2 


GE-SS 


47D221813G2 


AN -3 


PQ477 


Cordwood Module A3 


GE-SS 


47D221797G1 


!UH -4 


PQ246 


Cordwood Module A5 


GE-SS 


47D221798G1 KN -5 


Pq217 


Cordwood Ifodule A6 


GE-SS 


47D221796G1 1^ -4 


PQ635 


Cordwood Module A7 


GE-SS 


47D221799G1 1^ -4 


PP88i 


Cordwood Module A8 


GE-SS 


47E22180OG1 1^ -3 


PP882 


Stick Module A9 


GE-SS 


47E221801G1 


Sone 


PQ415 


Stick Module A12 


GE-SS 


47E221804G1 


AN -1 


PQ315 


Stick Module Ai3 


GE-SS 


47E221808G1 


Sone 


PP689 


Stick Module A14 


GE-SS 


47E221806G1 


AN -2 


PP690 


Stick Module A15 


GE-SS 


47E221807G1 


\N -1 


PP687 


Cordwood Module A16 


GE-SS 


47E221852G1 


iN -2 


PP815 


Stick Module A17 


GE-SS 


47E221853G1 


AN -3 


PP836 


Cordxoood Module A18 


GE-SS 


47D221851G1 


AN -5 


PQ386 


Chassis Ass'y A3 


GE-SS 


47D221811G1 


AN -4 


PQ43i 


P.C. Bd. Ass'y Al 


GE-SS 


47D22i918Gl 


AB -6 


PQ349 


Rect. & Filter Module A2 


GE-SS 


47D221793G1 


Sone 


PP4i5 


P.C. Bd. Ass'y A3 


GE-SS 


47D221919G1 


AN -5 


PQ350 


Rect. & Filter Module A4 


GE-SS 


47D221793G1 


tone 


PP238 


SEP, & UNFOLD TIMER 


GE-SS 


47E210587G1 


\N -2 


6549349 


Comp. Assy. Al 


GE-SS 


47E210585G1 


^ -1 


P0501 


AUX LOAD PANEL #1 


GE-SS 


47E210850G3 


VN -11 


6549346 


AUX LOAD PANEL #2 


GE-SS 


47E2i0850G3 


^ -11 


6549345 


TELtMtTKY CONVERSION MODULE #1 


GE-SS 


47E207682G1 


kN -15 


6549337 


TELiiMETRY CONVERSION MODULE #2 


GE-SS 


47E207682G1 


AN -15 


6549338 


TELEMETRY CONVERSION MODULE #3 


GE-SS 


47E207682GI 


AN -15 


6549334 


UNFOD) SWITCH 




133B1943P2 


AN-4 


4-32116 










Page 2 










Rev. A 



A-14 



CONSOLIDATED CONFIGURED ARTICLES LIST 





ERTS SPACECRAFT 903 






NOMSMCLATUME 




OWO • FART NO 


1 BKV 


• C R 1 A 1. HO. 


AUX. PROCESSING UNIT 


GE-SS 


47E221855-G1 


AN -14 


6549502 


Housing Assy. 1 


GE-SS 


47E221899-G1 


AN-6 


N/A 


IC Chassis Assy. 2 


GE-SS 


47E221884-G1 


AN-4 


PP906 


Module AL 


GE-SS 


47E221861-G1 


AN -3 


PP216 


Module A2 


GE-SS 


47E22I862-G1 


AN-1 


PP281 


Module A3 


GE-SS 


47E22186I-G1 


AN-3 


PP210 


Module A4 


GE-SS 


47E221862-G1 


AN-1 


PP412 


Module A5 


GE-SS 


47E221867-G1 


AN-3 


PP172 


Module A6 


GE-SS 


47E221868-G1 


AN-6 


PP196 


Module A7 


GE-SS 


47E221868-G1 


AN-6 


PP179 


Module A8 


GE-SS 


47E221865-G1 


AN-2 


PP253 


Module A9 


GE-SS 


47E221866-G1 


AN-2 


PP171 


Module AlO 


GE-SS 


47E221863-G1 


AN-1 


PP170 


Module All 


GE-SS 


47E221864-G1 


AN-3 


PP203 


Module A12 


GE-SS 


47E221869-G1 


AN-2 


PP173 


Module A13 


GE-SS 


47E221870-G1 


AN-1 


PP174 


Module A14 


GE-SS 


A7E221871-G1 


AN-2 


PP209 


Module A15 


GE-SS 


47E221872-G1 


AN-1 


PP244 


Module A 16 


GE-SS 


47E221873-G1 


AN-2 


PP227 


Module A17 


GE-SS 


47E221874-G1 


AN-1 


PP178 


Module A18 


GE-SS 


47D221875-G1 


AN-1 


PP418 


Module A19 


GE-SS 


47D221881-G1 


AN-6 


PP198 


Module A20 


GE-SS 


47D221875-G1 


AN-1 


PP417 


Module A21 


GE-SS 


47D221881-G1 


AN-6 


PP195 


Module A22 


GE-SS 


47D221882-GI 


AN-2 


PP150 


Module A23 


GE-SS 


47D221880-G1 


AN-3 


PP199 


Module A24 


GE-SS 


47D221875-G1 


AN-1 


PP416 


Module A25 


GE-SS 


47D221881-G1 


AN-6 


PP197 


Module A26 


GE-SS 


47D221876-G1 


AN-3 


PP204 


PC Bd. Assy. A27 


GE-SS 


47D221894-G1 


AN-6 


PP533 


PC Bd. Assy, A28 


GE-SS 


47D221897-G1 


AN-1 


PP901 


Module A29 


GE-SS 


47D221906-G1 


AN-4 


Unknown 


WB FREQ. MOD. ASS'Y. 


GE-SS 


47E221815G1 


AN -9 


6549505 


PW Board Ass'y Al 


GE-SS 


47E221832G1 


AN-7 


PQ286 


PW Board Ass 'y A2 


GE-SS 


47E221832G1 


AN-7 


PQ444 


PW Board Ass 'y A3 


GE-SS 


47D221830G1 


AN-3 


PQ192 


PW Board Ass'y A4 


GE-SS 


47D221834G1 


AN-4 


PQ037 


PW Board Ass'y A5 


GE-SS 


47E221826G1 


AN-6 


PQ015 


PW Board Ass 'y A6 


GE-SS 


47E221828G1 


AN -5 


PQ038 


PW Board Ass'y A7 


GE-SS 


47E221830G1 


AN-3 


PQ284 


PW Board Ass'y A8 


GE-SS 


47D221836GI 


AN-8 


PQ334 


PW Board Ass'y A9 


GE-SS 


47D221836G1 


AN-8 


PQ597 


Ref. Osc. X4 Mult. All 


GE-SS 


47E223316G1 


AN-2 


PQ039 


Volt Reg/VCO AI5 


GE-SS 


47E22331IG1 


AN-7 


PQ026 


Volt Reg/VCO A16 


GE-SS 


47E223311G1 


AN-7 


PQ025 


Volt Reg/VCO A17 


GE-SS 


47E223311G2 


AN-7 


PQ028 


Volt Reg/VCO A18 


GE-SS 


47E223311G2 


AN-7 


PQ027 


Diode Module A19 


GE-SS 


47E223380G1 


AN-1 


PQOOl 


Stripline 


GE-RESD 


47D178444G1 


Rev F 


My583-Al 


Dis. If. Lim. A12 


GE-RESD 


47C148186P1 


ReTMB 


MY585-A1 1 



Page 3 
Revision A 



A^15 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



NO MK MCI. A TUNC 




owe • l>ART MO 


RKV 


•■RIAL MO. 


TEMPERATURE CONTROLLER -BAY 1 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549466 
FX566.A92 


TEMPERATURE CONTROLLER -BAY 2 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549460 
FX566-A93 


TEMPERATURE CONTROLLER -BAY 3 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549379 
FX566-A20 


TEMPERATURE CONTROLLER -BAY 4 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
'aN-2 


6549378 
FX566-A35 


TEMPERATURE CONTROLLER -BAY 5 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549465 
FX566-A57 


TEMPERATURE CONTROLLER -BAY 7 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549459 
FX566-A62 


TEMPERATURE CONTROLLER -BAY 8 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549456 
FX566-A78 


TEMPERATURE CONTROLLER -RAY 9 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549464 
FX566-A64 


TEMPERATURE CONTROLLER-BAY 10 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633PI 


AN-7 
AN-2 


6549474 
FX566-A76 


TEMPERATURE CONTROLLER-BAY 11 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549455 
FX566-A79 


TEMPERATURE CONTROLLER-BAY 12 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549386 
FX566-A41 


TEMPERATURE CONTROLLER-BAY 13 
Bellows 


GE-SS 
Flexoni cs 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549380 
FX566-A8 


TEMPERATURE CONTROLLER-BAY 14 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 

AN-2 


6549458 
FX566-A73 


TEMPERATURE CONTROLLER-BAY 15 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549457 
FX566-A58 


TEMPERATURE CONTROLLER- BAY 16 
Bellows 


GE-SS 
Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549461 
FX566-A77 


TEMPERATURE CONTROLLER-BAY 17 
Bellows 


GE-SS 

Flexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549462 
FX566-A49 


TEMPERATURE CONTROLLER-BAY 18 
Bellows 


GE-SS 
i'lexonics 


47E213640G5 
47C213633P1 


AN-7 
AN-2 


6549463 
FX566-A70 



Page 4 



A--16 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



MOMCHCLATURE 


Sur^LIKR 


□ wo * FART MO, 


QKV 


• KRtAt. HO. 


WBFM POWER SUPPLY 


GE-SS 


47E223321G1 


AN-11 


6549508 


Post Reg. Ass'y 


GE-SS 


47D223325G1 


AN-5 


PP913 


XSTR Brkt. Ass'y 


GE-SS 


47B223342G2 


AN-B 


PQ193 


Pwr Trans. Ass'y 


GE-SS 


47D223356G1 


AN-1 


PQ720 


Pwr Trans. Ass'y 


GE-SS 


47D223356G1 


AN-1 


PQ721 


Conv. Ass'y Al 


GE-SS 


47D223305G1 


AN-5 


PP870 


Conv. Ass'y A3 


GE-SS 


47D223305G2 


AN-5 


PP871 


Cap Module A5 


GE-SS 


47E223309G1 


Hone 


PP532 


Diode Module A6 


GE-SS 


47D223310G1 


AN-1 


PP530 


Rect. Ass'y A7 


GE-SS 


47C223324G1 


AN-2 


PP897 


Rect. Ass'y A8 


GE-SS 


47C223324G1 


AN-2 


PP898 , 


Diode Ass'y A9 


GE-SS 


47C223349G1 


None 


PP877 


POWER SWITCHING MODULE 


GE-SS 


47E221925G2 


AN-11 


6549501 


Relay Ass'y Al 


GE-SS 


47D221936G1 


AM-1 


PQ593 


Relay Ass'y A2 


GE-SS 


47D221956G1 


AN-1 


PQ589 


Relay Ass'y A3 


GE-SS 


47D221956G1 


AN-1 


PQ592 


Relay Ass'y A4 


GE-SS 


47D221956G1 


AM-1 


PQ591 


Relay Ass'y A5 


GE-SS 


47D221956G1 


AN-1 


PQ590 


Telem. Resistor Ass'y 

A6 
Diode Ass'y A7 


GE-SS 


47D221954G1 


AN-3 


PQ587 


GE-SS 


47D221955G1 


AN-2 


PQ588 


Fuse Ass'y A8 


GE-SS 


47D221953G1 


AN-2 


PQ585 


Fuse Ass'y A9 


GE-SS 


47D221953G2 


AN-2 


PQ586 


Relay Bd Ass'y AlO 


GE-SS 


47D221886G1 


AN-3 


PQ434 


Relay Panel, Top All 


GE-SS 


47D221969G2 


AN -4 


PS 148 


Relay Panel, Bot. A12 


GE-SS 


47D22i970G2 


AN-5 


PS273 


COMMAND RECEIVER 


RCA 


2271145-502 


R 


EAB-FT2 


A4 Receiver Assembly 


RCA 


2270108-501 


F 


003 


Al IF Amp. Board 


RCA 


2271156-501 


D 


001 


A2 IF Amp, Board 


RCA 


2271156-501 


D 


002 


A3 Osc. & RF Amp. Board 


RCA 


2270106-501 


C 


001 


AA Osc. & RF Amp. Board 


RCA 


2270106-501 


c 


002 


Demodulator Comp. 


RCA 


2271154-501 


K 


06 


Demodulator Comp. 


RCA 


2271154-501 


K 


07 


Regulator & Telemetry 


RCA 


2271153-501 


F 


03 


Antenna Coupler 


RCA 


2262728-501 


B 


06 


Diode Board Assembly 


RCA 


1974688-501 


A 


03 


Comp. Board Assembly 


RCA 


2262746-501 


E 


05 


RBV MMCA 


GE-SS 


47D224600G1 


AN-2 


6549513 


Coil Housing 


GE-SS 


47D224605C1 


None 


DJ098 


Panel Assembly 


GE-SS 


47C224608G1 


AN-3 


PRO 10 


Coil Assembly 


GE-SS 


47D224602G1 


AN-2 


PQ900 



Page 5 



A-17 



CONSOLIDATED CONFfGURED ARTICLES LIST 



ERTS SPACECRAFT 903 



N O M C M C L A T U R E 


^,U^^i.tlft 


pwq * ^AWT MO 


»■ V 


• KHIAL Mo'. 


DCS RECEIVER "A" 


Radiation 


613310G1 


CI 


EAB-FT2 


Preselector Assembly 


Radiation 


529220Gi 


A 


0003 


Second IF 


Radiation 


12422601 


CI 


0002 


Limiter 


Radiation 


124227G1 


A 


0002 


Relay 


Radiation 


124228G1 


A 


0008 


First IF 


Radiation 


124229G1 


CI 


0003 


R*F, Amplifier 


Radiation 


i24230Gl 


BI 


0006 


Power Supply 


Radiation 


12423 IGI 


A 


0002 


Osc. 6c X6 VHF Receiver 


Radiation 


124232G1 


A 


0002 


First Doubler 


Radiation 


124233G1 


A 


0003 


Second Doubler 


Radiation 


124234G1 


A 


0002 


Buffer Amplifier 


Radiation 


124609G1 


A 


0002 


DCS RECEIVER "B" 


Radiation 


613310G1 


CI 


EAB-Fr3 


Preselector Asseinbly 


Radiation 


529220G1 


A 


0006 


Second IF 


Radiation 


124226G1 


CI 


0003 


Limiter 


Radiation 


124227G1 


A 


0003 


Relay 


Radiation 


124228G1 


A 


0006 


First IF 


Radiation 


124229G1 


CI 


0002 


R.F* Amplifier 


Radiation 


124230Gt 


Bl 


0008 


Power Supply 


Radiation 


124231G1 


A 


0003 


Osc* 6c X6 VHF Receiver 


Radiation 


124232G1 


A 


0003 


First Doubler 


Radiation 


124233G1 


A 


0001 


Second Doubler 


Radiation 


124234G1 


A 


0001 


Buffer Amplifier 


Radiation 


124609G1 


A 


0003 


PREMOD. PROCESSOR 


SCI 


2600000-1 


A 


EAB-FT2 


Electronics Assy* 


SCI 


2600060-1 


A 


003 


PCB Assy., Pwr, Filter 


SCI 


2600037-1 


A 


002 


PCB Assy,, Pwr* Supply 


SCI 


2600049-1 


A 


002 


PCB Assy., Pwr. Supply 


SCI 


2600049-1 


A 


007 


PCB Assy,, Sec. Sw. 


SCI 


2600068-1 


B 


005 


PCB Assy., Tape Rec. Sw- 


SCI 


2600043-1 


B 


003 


PCB Assy., 597KHZ Mod. 


SCI 


2600031-1 


A 


003 


PCB Assy,, 768KHZ Mod. 


SCI 


2600034-1 


B 


001 


PCB Assy. , CSSN 


SCI 


2600046-1 


A 


004 


PCB Assy* , Discriminator 


SCI 


2600040-1 


A 


006 


PCB Assy., Discriminator 


SCI 


2600040-1 


A 


002 


AUK LOAD CONTROLLER 


GE-SS 


47E210783G4 


AN- 10 


6549352 


Relay Panel Al 


GE-SS 


47E2 1078 IGI 


AN- 11 


PP134 


Relay Panel A2 


GE-SS 


47E210787G1 


AN- 14 


P0573 


ADAPTER 


GE-SS 


47J213521G1 


AN-2 


010 


PREFLIGHT DISCONNECT 


KINETICS 


47E211225P2 


None 


0012 


SEPARATION SWITCHES (ADAPTER) 


M1NN,-H 1 


133B1902P2 


AN-5 


212, 215 


SEPARATION SWITCHES (SPACECRAFT 


MlNN,-n 1 


I33B1902P2 


AN -5 


209, 211 










Page 6 










Rev* A 



A-18 



CONSOLIDATED CONFIGURED ARTICLES LIST 





ERTS SPACEC 


RAFT 903 






HOME Hei.Arun E 


9Um.lCR 


Dwo * i*Aitr NO, 


RKV 


•SRIAL MO. 


Unified S-Band Equipment 


Motorola 


01-P09566C001 


E 


EAB - QM 


Frequency Multiplier 1A7 




01-P09568C001 


C 


A102 


Frequency Multiplier 1A17 




01-P09568C001 


c 


AlOl 


Wide Band Detector 1A4 




01-PO9570COdl 


D 


A102 


Limiter Amplifier AROOl 




01-P09627C001 


None 


Alll 


Limiter Amplifier AR002 




01-P09627C001 


None 


Alls 


Limiter Amplifier AR003 




01-P09627C001 


None 


A102 


Limiter Amplifier AR006 




01-P09627C001 


None 


A104 


Divider 19-9. SMC A002 




01-P09632C001 


A 


A102 


Buffer Amplify 9.5MC AR005 




01-P09635C001 


None 


A102 


Signal Driver AOOl 




01-P0964AC001 


B 


A102 


Ref Driver A003 




01-P09646C001 


B 


A102 


Subcarrier Amp. AR007 




01-P09648C001 


None 


A102 


Ranging Ampl. AR004 




01-P09650C001 


A 


A102 


Wide Band Detector 1A14 




01-P09570C001 


D 


AlOl 


Limiter Amp. AROOl 




01-P09627C001 


None 


AlOl 


Limiter Amp. AR002 




01-P09627C001 


None 


A 106 


Limiter Amp. AR003 




01-P09627C001 


None 


A109 


Limiter Amp. AR006 




01-P09627C001 


None 


Alio 


Divider 19-9. SMC A002 




01-P09632C001 


A 


AlOl 


Buffer Amp. 9. SMC AR005 




01-P09635C001 


None 


AlOl 


Signal Driver AOOl 




01-P09644C001 


B 


AlOl 


Ref. Driver A003 




01-P09646C001 


B 


AlOl 


Subcarrier Amp. AR007 




01-P09648C001 


None 


AlOl 


Ranging Amp. AR004 




01-P096S0C0ai 


A 


AlOl 


Auxiliary Osc, PM 1A9 




01-F095S3C001 


H 


AlOl 


Switching Network. AOOl 




01-P09557C001 


None 


AlOl 


Auxiliary Osc, PM 1A19 




01-P09553C001 


H 


A 102 


Switching Network AOOl 




01-P09557C001 


None 


A103 


Voltage Control Osc. 1A8 




O1-PO9548C0OI 


F 


AlOl 


Voltage Control Osc 1A18 




01-P09548C001 


F 


A102 


Narrow Band Detector 1A2 




01-P09544C001 


E 


A102 


Narrow Band Detector 1A12 




01-P09544C001 


E 


AlOl 


IF Amplifier Mixer lAl 




01-P09540C001 


D 


A102 


IF Amplifier Mixer lAll 




01-P09S40C001 


D 


AlOl 


RF Converter 1A3 




Ol-P09572COai 


E 


AlOl 


RF Converter 1A13 




01-P09S72C001 


£ 


A 104 


Pow. Amp/X30 Mult PM lAlO 




O1-P09585CO01 


H 


AlOl 


Helical Resonator AD02 




01-P09658C001 


None 


AlOl 


Filter-Power Amp. AOOl 




01-P09711C001 


None 


AlOl 


Freq. Mult X3 




01-K)9714C001 


A 


Aldl 


S Band Power Amp. 




01-P09589C001 


F 


AlOl 


Pow. Amp/X30 Mult PM 1A20 




01-P0958SC001 


H 


A102 


Helical Resonator A002 




01-P09658C001 


None 


A102 


Filter- Power Amp. AOOl 




O1-P09711C001 


None 


A102 


Freq. Mult X3 




01-P09714C001 


A 


A102 


S Band Power Amp 




01-P09589C001 


F 


A 104 


Diplexer 1A21 




01-P09602C001 


D 


A102 


Power Converter XMTR 1A5 




01-P09577C001 


G 


AlOl 


Regulator AOOl 




01-P09689C001 


C 


A 104 



Page 7 



A-19 



CONSOLIDATED CONFIGURED ARTICLES LIST 



ERTS SPACKCRAFT 903 



HOMCHCLATUIIE 



Unified S-Band Equip. (Cont.) 



Power Converter XMTR 

Regulator 
Power Converter RCVR 

Regulator 
Power Converter RCVR 

Regulator 
Connector/EMI Box 
Cable Assembly Wl 
Cable Assembly W2 
Cable Assembly W3 
Cable Assembly W4 
Cable Assembly W5 
Cable Assembly W6 
Cable Assembly W7 
Cable Assembly W8 
Cable Assembly W9 
Cable Assembly WlO 
Cable Assembly Wll 
Cable Assembly Wl2 
Cable Assembly W13 
Cable Assembly W14 
Cable Assembly W15 
Cable Assembly W16 
Cable Assembly Wl7 
Cable Assembly W18 
Cable Assembly W19 
Cable Assembly W20 
Cable Assembly W21 
Cable Assembly W22 
Cable Assembly W23 
Cable Assembly W24 
Cable Assembly W25 
Cable Assembly W26 
Cable Assembly W27 
Cable Assembly W28 
Cable Assembly W29 
Cable Assembly W30 
Cable Assembly W31 
Cable Assembly W32 
Cable Assembly W33 

Wide Band Filter #1 

Wide Band Filter #2 



1A15 
AOOl 

1A6 
AOOl 

1A16 
AOOl 

1A22 



Motorola 



o wo % ^A WT tto 



Peninsula 



01-PO9577C001 

0X-P09689C001 

01-PO9740C001 

01-P09689C001 

01-P09740C001 

01-P09689C001 

01-P09604C001 

30-P02306D001 

30'P02306D002 

30-P02306D003 

30-P02306D004 

30-P02306D005 

30-P02306D006 

30^P02306D007 

30-P02306D008 

3O-PO2306D0O9 

30-P02306D010 

30-P02306D011 

30>P02306D012 

30-P02306D013 

30'P02306D014 

30-P02306D015 

30'P02306D016 

30-P02306D017 

30-P02306D018 

30-P02306D019 

3O-PO2306D02O 

30-P02306D02I 

30-P02306D022 

30-P02306D023 

30-P02306D024 

30-P02319D001 

30-P02307D001 

30-P02307D002 

,30-K)2318D001 

30-P02317D001 

30-P02320D001 

30-P02321D001 

30-P02306D025 

30-P02306D026 

Model F1522B 



Peninsula Model F1522B 



REV 



G 
C 
G 
C 
G 
C 
G 
D 
D 
D 
D 

b 

D 
D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

D 

B 

B 

B 

C 

B 

*C 

B 

D 

D 

None 

None 



• Cll I Al. 



EAB-QM 
(continued) 

A102 

A102 

A102 

A103 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

A102 

A102 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

AlOl 

A102 

AlOl 

AlOl 

AlOl 

4 

8 



Page 8 



A-20 



CONSOLIDATED CO N F IGU R E D AR T I CL E S LIST 





ERTS SPACECRAFT 903 






NOMENCt-ATunC 


SU^PUIC R 


Qwa • PART NO 


RKV 


• CR 1 Al. HO. 


POWER SUBSYSTEM 


RCA 








CONTROL MODULE 


RCA 


1759712-502 


AG 


010 


A-1 Fuse Board Assy. 


RCA 


1759561-501 


G 


017 


A-2 Fuse Board Assy. 


RCA 


1759561-502 


G 


019 


A-3 C.F. Regulator Board 


RCA 


1759567-501 


B 


020 


A-4 C.F. Regulator Board 


RCA 


1759567-501 


B 


017 


A-5 Regulated Buss 


RCA 


1759570-501 


E 


015 


A-6 Aux. Reg. £■ Trickle 


RCA 


1759569-501 


C 


015 


A-7 Shunt Dis. Dr. Telem. 


RCA 


1759577-501 


F 


015 


A-8 Current, Sens. & Telem. 


RCA 


1759582-501 


D 


015 


A-9 Harness Assy. 


RCA 


1849873-501 


E 


017 


A-10 Sw. Bd. Assy. 


RCA 


1966502-501 


C 


015 


A-11 Diode & Fil. Bd. Assy. 


RCA 


1966505-501 


C 


015 


A-12 Filter Board Assy. 


RCA 


1965840-501 


None 


015 


A-i3 Cap. Assy. 


RCA 


1768958^501 


B 


016 


A-14 Cap. Assy. 


RCA 


1768757-501 


B 


015 


A-15 Heat Sink Assy. 


RCA 


1849560-501 


D 


015 


A-16 Bracket Heat Sink Assy. 


RCA 


1768982-501 


C 


015 


A-17 Filter Assy. 


RCA 


2263400-501 


G 


015 


Inductor Assy. 


RCA 


1768483-501 


D 


015 


Inductor Assy. 


RCA 


1768941-501 


C 


015 


PAY LOAD REGULATOR MODULE 


RCA 


1759712-503 


AG 


Oil 


A-1 Fuse Board Assy. 


RCA 


1759561-501 


G 


002 


A-2 Fuse Board Assy. 


RCA 


1759561-502 


G 


019 


A-3 C.F. Regulator Board 


RCA 


1759567-501 


B 


018 


A-4 C.F. Regulator Board 


RCA 


1759567-501 


B 


016 


A-5 Regulated Buss 


RCA 


1759570-501 


E 


016 


A-6 Aux. Reg. & Trickle 


RCA 


1759569-501 


C 


016 


A-7 Shunt Dis. Dr. Telem. 


RCA 


1759577-501 


F 


016 


A-S Current, Sens. & Telem. 


RCA 


1759582-501 


C 


016 


A-9 Harness Assy. 


RCA 


1849873-501 


E 


018 


A-10 Sw. Bd, Assy. 


RCA 


1966502-501 


C 


016 


A-11 Diode & Fil. Bd. Assy. 


RCA 


1966505-501 


C 


016 


A-12 Filter Board Assy. 


RCA 


1965840-500 


None 


016 


A-13 Cap. Assy. 


RCA 


1768958-501 


B 


019 


A-14 Cap, Assy. 


RCA 


1768757-501 


B 


016 


A-15 Heat Sink Assy. 


RCA 


1849560-501 


D 


016 


A-16 Bracket Heat Sink Assy. 


RCA 


1768982-501 


C 


016 


A-17 Filter Assy. 


RCA 


2263400-501 


E 


016 


Inductor Assy. 


RCA 


1768483-501 


D 


016 


Inductor Assy. 


RCA 


1768941-501 


C 


016 


SOLAR PLATFORM 6i ARRAY 


RCA 


2271152-501 


B 


102 


Platform Motor Drive 


RCA 


2271118-501 


F 


101 


Motor Mount Subassembly 


RCA 


2271109-501 


G 


101 


Drlvo Motor Assy. 


RCA 


1751589-501 


D 


113 


Motor 


RCA 


1751588-1 




101 


SOLAR PLATFORM & ARRAY 


RCA 


2271152-502 


B 


102 


Platform Motor Drive 


RCA 


2263808-501 


M 


104 


Motor Mount Subassembly 


RCA 


1976768-501 


K 


104 


Drive Motor Assy. 


RCA 


1751589-501 


D 


112 


Motor 


RCA 


1751588-1 




033 



Page 9 

Rev. A A^21 



CONSOLIDATED CONFiGURED ARTICLES LiST 

ERTS SPACECRAFT 903 





ir<>M t ifct A^uAc 


9UP^LlKR|ovyG * PAKT Moj 


a»v 






a&TTERY MDDUU ASK 


RCA 


2265943-501 


K 


57 




Electronic fd. 


RCA 


1759578-502 


J 


59 




Electronic id. 


RCA 


1849843-502 


G 


59 




Relay & Herncs^, Bkt« Assy* 


RCA 


1849822-502 


E 


65 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


57 




MTTERY MODULE ASSY 


RCA 


2265943-501 


K 


58 




Electronic Bd. 


RCA 


1759578-502 


J 


62 




Electronic Bd. 


RCA 


1849843-502 


G 


62 




Rei*y £[ Harness, Bkt. Assy. 


RCA 


1849822-502 


E 


58 




Heat Sink, Wiring Assy, 


RCA 


1849598-502 


G 


58 




BAITERY MODULE ASSY 


RCA 


2265943-501 


K 


59 




Electronic Bd. 


RCA 


1759578-502 


J 


61 




Electronic Bd* 


RCA 


1849843-502 


G 


61 




Relay & Harness, Bkt. Assy, 


RCA 


1849822-502 


E 


59 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


59 




BATTERY tODULE ASSY 


RCA 


2265943-501 


K 


60 




Electronic Bd. 


RCA 


1759578-502 


J 


60 




Electronic Bd. 


RCA 


1849843-502 


G 


60 




Relay 6c Harness, Bkt, Assy. 


RCA 


1849822-502 


G 


55 




Heat Sing, Wiring Assy. 


RCA 


1849598-502 


G 


60 




EilTTE&Y MODULE ASSY 


RCA 


2265943-501 


K 


hi 




Electronic Bd. 


RCA 


1759578-502 


J 


63 




Electronic Bd, 


RCA 


1849843-502 


G 


63 




Relay 6( Harness, Bkt. Assy. 


RCA 


1849822-502 


E 


61 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


61 




BATTERY MODULE ASSY 


RCA 


2265943-501 


K 


62 




Electronic Bd, 


RCA 


1759578-502 


J 


65 




Electronic Bd. 


RCA 


1849843-502 


G 


65 




Relay & Harness, Bkt. Assy. 


RCA 


1849822-502 


E 


62 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


62 




BATTERY MODULE ASSY 


RCA 


2265943-501 


K 


63 




Electronic Bd. 


RCA 


1759578-502 


J 


66 




Electronic Bd. 


RCA 


1849843-502 


G 


66 




Relay & Harness, Bkt. Assy, 


RCA 


1849822-502 


E 


63 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


63 




BATTERY MODULE ASSY 


RCA 


2265943-501 


K 


64 




Electronic Bd, 


RCA 


1759578-502 


J 


64 




Electronic Bd. 


RCA 


1849843-502 


G 


64 




Relay & Harness, Bkt. Assy. 


RCA 


1849822-502 


E 


64 




Heat Sink, Wiring Assy. 


RCA 


1849598-502 


G 


64 



A-22 



Pase 10 



CONSOLIDATED CONFIGURED ARTICLES LIST 



EKl 


:S SPACECRAFT 903 






HOMCMCLATUH E 




Dwo * fAItT MO 


as V 


•■RIAL MO. 


VERSATILE INFORMATION PROCESSOl 


RADIATION 


6076AOG10 


B3 


FLT-001 


Reprogrammer 




6081AIG5 


Dl 


005 


Elec. Assy. 




608140G3 


B 


0005 


Serial Regulator 




520110G2 


C 


0005 


Command Relays 




520111G4 


D 


0005 


Command Relays 




520112G2 


C 


0005 


Output liuffer Amplifier 




520113G2 


CI 


0005 


Heat Sink 




411483G2 


C 


0005 


Digital Multiplexer 




608091G6 


'02 


005 


Elec. Assy. 




608090G6 


Gl 


0005 


Dig. Gates Assy. Al 




520060G2 


A 


0017 


Dig, Gates Assy. A2 




520060G2 


A 


0018 


Dig. Gates Assy. A3 




520060G2 


A 


0020 


Dig. Gates Assy. A4 




520060G2 


A 


0019 


Dig. Sequencer Assy. A5 




52006 2G2 


A 


0006 


Decoder Matrix A6 




520063G2 


B 


0005 


DC/DC Converter P.S. A7 




520081G1 


A 


0004 


Out. Reg. i. T.C. Buffer A8 




520086G1 


A 


0008 


Out. Reg. & T.C. Buffer A9 




520086G1 


A 


0007 


Dig. Add. d Ser. Data AID 




520087G1 


C 


0008 


Dig. Add. & Sor. Data All 




520087G1 


C 


0007 


Dig. Ctr.& CMD. A12 




520089G2 


B2 


0006 


Dig. Ctr. & CMD A13 




5 2 008 9G 2 


B2 


0005 


Formatter, DC/DC Conv. AlA 




520085G1 


A 


0004 


Dig. Interface Buff. A15 




520084G1 


B 


0008 


Dig. Interface Huff. A16 




520084G1 


B 


0007 


Memory Sequencer 




60824 1G3 


E2 


005 


Elec. Assy. 




608 24 OG 3 


CI 


0005 


Cent & Out Keg Assy Al 




520232G1 


D 


0008 


Funct Gen 6i Repr Assy A2 




520233G1 


Dl 


0008 


Instr Ctr ^c Comp Assy A3 




520234G2 


Dl 


0008 


Cont & Output Reg Assy AA 




520232GI 


D 


0007 


Funct Gen & Repr Assy A5 




520233G1 


Dl 


0007 


Instr Ctr £. Comp Assy A6 




520234G2 


Dl 


0007 


DC/DC Converter Assy A7 




520235G1 


D 


0004 


Memory A 




608191G9 


D2 


008 


Elec. Assy. 




608190G9 


Fl 


0008 


Section I Assy. Al 




520170G3 


Gl 


0001 


Mom. Amp. Assy, Sec I 




520161G4 


El 


0018 


Memory Array Assy, Sec II 




519218C3 


C 


0001 


Memory Array, Sec. I 




520I68G3 


C 


0014 


Mem. Amp, Assy. Sec, T 




520161r^ 


D 


0016 


Decode Assy Sec, 1 ^\ III. A 2 




52()l84(;l 


D 


0006 


Bit Driver, Sot IF A3 




52nia3(;3 


n2 


0006 


H.l). .s, Data Kej;. Sec in AA 




'j:'oi86(;2 


D 


0006 


Decoder, Sec. IL A5 




520183G1 


C 


0006 


Assy, Sec. II tS LLl A6 | J 


520171(;3 


D2 


0001 1 



ORIGINAL PArt- ,„ 



Page 11 

A-23 



CONSOLIDATED CONFIGURED ARTICLES LIST 





ERTS SPACECRAFT 903 






HOM E MCLATUR C 




O W O * PAItT NO 


aa V 


• krial mo! 


V.I, P. (continued) 






^^■■" 




Memory A (continued) 








(008) 


Menu Array Assy, Sec XL 




519218G'^ 


C 


0004 


Mcin. Array Sec II 




520168G4 


C 


0017 


Metiu Amp Assy II ^ 111 




520182C2 


Dl 


0006 


Mem* Array Assy, Corv 




519220G2 


El 


0001 


Mem, Array Assy, Core 




520169G2 


B 


0008 


1k:/DC Converter A7 




520187G1 


CI 


0007 


Mumory B 




608191G10 


D2 


009 


KleCo Assy* 




608190G10 


Fl 


0009 


Section I Assy^ Al 




520170G3 


Gl 


0002 


Mem. Am]). Assy, Sec I 




520161G4 


El 


0015 


Memory Array Assy, Sec 11 




519218G3 


Dl 


0003 


Memory Array Sec. 1 




52()16aGJ 


C 


0016 


Menu Ani]i. Assy^ See, 1 




520161G4 


El 


0017 


Deeotle Assy Sec I ^ li A:! 




520184G1 


El 


0007 


Kit Driver, Sec iX At 




520185(;3 


fi2 


0007 


P>J). ^ Data KuK Sec XL A'\ 




52(n80G2 


D 


0007 


Decoder, Sec, II A'5 




3?01Ki(;l 


C 


0007 


Atisy, Sue. 11 ^ TIJ. Ab 




52017 ItV) 


D2 


0002 


Mem. Array Assy, Sec TI 




5].y218t:4 


Dl 


0005 


Mem. Array, Sec II 




520168G4 


C 


0018 


Mem„ Amp, Assy, H ^ Til 




520182(;2 


Dl 


0007 


Mem, Array Assy, Core 




319220G2 


El 


0002 


Mem* Array Assy, Core 




520169G2 


B 


0009 


DC/DC Converter A7 




520187G1 


CI 


0008 


Analog Multiplexer 




60804 1g5 


Dl 


005 


i:lec. Assy. 




608040G3 


El 


0005 


Coder. Analog Assy Al 




520033C1 


E2 


0007 


nc/Dt: Conv. Card Assy. A2 




520034G1 


B2 


0008 


DC /DC Conv. Card Assy. A3 




520034G1 


B2 


0007 


Coder Analog Assy. AA 




52O033G1 


E2 


0008 


Analog Matrix Assy, A3 




520031G1 


A 


0008 


DC /DC Conv. 6cpwr. Assy A6 




520032(11 


CI 


0004 


Analo^^ Matrix Assy. A/ 




52(K):U(;l 


A 


0007 


Analog ralfS Assy, A^^ 




52()030G1 


H 


0055 


Analog', Cates Assy A') 




5:.'i)o;j()(;i 


li 


0030 


Anal OK Calebs Assy. Alo 




52m)ju(;l 


B 


0032 


AnaloK Cates Assy. All 




52003U(:l 


B 


0036 


Analog Crates Assy. A12 




520030G1 


B 


0035 


Analog Cates Assy. A13 




320030(;l 


B 


0034 


Analog Cates Assy. Al^ 




520030G1 


B 


0031 


Analog Cates Assy. A15 




520030C1 


B 


0029 


Analog Cates Assy. A16 




52OO30G1 


B 


0028 



Page 12 



A-24 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECEAFC 903 



NOMKHC1.ATUKE 



9UI 



DWG * PART MO, HKV 



•■RIAL NO 



^MCA 
Al Card 
Al Card 

Orbit Adjust Subsystem 
Thruster Assembly 
Thruster Assembly ; 
Thruster Assembly 
Trans. Box & Connector 

Attitude Measurement Sensor 
IR Telescope Assembly 
Housing Assembly 
Objective Lens Assembly 
Filter Assembly 
Heat Sink Assembly 
Chopper Board Assembly 
Signal Board - Lower 
Signal Board - Upper 
Signal Board Assembly 
Connector Assembly 
DC-DC Converter Bd. Assembly 
Regulator Board Assembly 
Output Board Assembly 

WIDEBAND POWER AMP. #1 

Traveling Wave Tube 
LV Pwr Supply Assy, 
Card Ass'y No. 1, LV 
Card Ass'y No. 2, LV 
HV Pwr Supply Ass'y 
Card Ass'y No. 1, HV 
Card Ass'y No. 2, HV 
Card Ass'y Turn-On Con, 
Cable Ass'y, RF 
Cable Ass'y, RF 
Cable Ass'y, RF 
Thermistor 



Ithaco 



Rkt.Rsrch 



Quant ic 



Watkins- 
Johnson 



D40634G4 
D40614G1 
D40615G1 

26058-9 
25111-49 

25111-49 
25111-59 
24949-5 

51877-01 
51788-01 
51903-01 
51791-01 
51797-01 
51807-01 
51878-01 
51849-01 
51853-01 
51909-01 
51907-01 
51873-01 
51883-01 
51890-01 

612970 

612965 
612982 
612984 
612986 
612980 
612997 
612999 
612944 
612977 
612978 
612979 
612957 



S 



C 


NEF-EAB-FT3' 


A 


11650 


A 


11653 


D 


FT3 


L 


319 


L 


325 


L 


3 04 A 


F 


103 


D 


FT2 


G 


003 


E 


003 


C 


003 


A 


003 


C 


003 


E 


005 


B 


004 


B 


004 


C 


004 


C 


004 


E 


004 


G 


004 


C 


004 


E 


pr4 


B 


11 


B 


405 


B 


405 


B 


405 


1 


405 


B 


305 


B 


305 


B 


405 


B 


39 


B 


26 


B 


22 


None 


10 



Page 13 



ORIGINAL PAGE IS 
OF POOR QUALITY 



A-25 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



HO Ml HCt.ATUA E 



WIDEBAND POWER AMPLIFIER #2 

Traveling Wave Tube 
LV Pwr Sujjply Ass'y 
Card Ass'y No* 1, LV 
Card Ass'y No, 2, LV 
HV Pwr Supply Ass'y 
Card Ass'y No. 1, HV 
Card Ass*y No. 2, HV 
Card Ass'y Turn-On Con. 
Cable Ass'y, RF 
Cable Ass'y, RF 
Cable Ass'y, RF 
Thermistor 

PCM TLN RECORDER #1 
Preamp, Digital 
Repr & Erase Con, Rec Logic 
Amplifier, Record/Repr. 
Motor Drive & Telemetry 
Transport Group Subass'y 
Lt» Source &. Sensor Ass'y 
Electronic Switch, Mtr Invt, 
Electronic Switch, Mtr Invt. 
Power Supply 

Vtg Reg 6c Current Telemetry 
Filter, EOT Backup 
Magnetic Tape 

PCM TLM RECORDER #2 

Preamp, Dig Repr & Erase 
Control, Recorder Logic 
Amplifier, Record/Repr. 
Motor Drive & Telemetry 
Transport Group Subass'y 
Lt. Source & Sensor Ass'y 
Electronic Switch, Mtr Invt. 
Electronic Switch, Mtr Invt* 
Power Supply 

Vtg Reg 6t Current Telemetry 
Filter, EOT Backup 
Magnetic Tape 



SUPFI-ltl 



Watkins- 
Johnson 

ji 
II 

n 

ir 
n 
11 
It 
ri 
II 
n 

Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 

Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 
Leach 



QwG » PAWT wo. a » V MEmtAL. NO 



612970 

612965 
612982 
612984 
612986 
612980 
612997 
612999 
612944 
612977 
612978 
612979 
612957 

202835-001 

202911-001 

202915-001 

202920-001 

202925-001 

202930-001 

202932-001 

202965-001 

202965-001 

202966-001 

202973-001 

11-16195 

1/4 - 551 

202835-001 

202911-001 

202915-001 

202920*001 

202925-001 

202930-001 

202932-001 

202965-001 

202965-001 

202966-001 

202973-001 

11-16195 

1/4 - 551 



FTS 



B 


8 


B 


404 


B 


404 


B 


404 


D 


404 


B 


404 


B 


404 


B 


404 


B 


38 


B 


27 


B 


23 


None 


006 


B 


EAB-QMl 


B 


911001. 


B 


915002 


B 


920001 


B 


925001 


A 


930001 


None 


932001 


None 


965001 


None 


965002 


None 


966001 


A 


973001 


A 


195001 


None 


508 


B 


EAB-FT4 


B 


911005 


B 


915001 


B 


920005 


B 


925005 


B 


930005 


None 


932005 


None 


965009 


None 


965010 


None 


966005 


A 


973005 


A 


195005 


None 


510 



Page 14 



A-26 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



M O M C M C I. A T U H C 



COMMAND CLOCK SUBASSEMBLY 
Motor Drive Ass'y 
Frequency Amplifier Ass'y 1 
Time Code Ass'y 
Frequency Amplifier Ass'y 2 
Comstor Memory Ass'y 
Comstor Logic Ass'y 
Comdec Ass'y 
Telemetry Ass'y 
Matrix Ass'y 
Power Supply #1 
Power Supply #2 
Oscillator (A) 
Oscillator (B) 

INTERFACE SWITCHING MODULE 

Relay Network No. 2B 

Relay Network No. 1 

Relay Network No. 1 

Relay Network No. 2B 
Resistor Network 

Relay Network No. 1 

Relay Network No. 2B 
Resistor Network 

Relay Network No. 4B 

Relay Network No. 2B 

Relay Network No. 1 

Relay Network No. 1 
Cable No. 1 



Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No. 
Cable No- 
Cable No. 



No 

Jtmiper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 

Jumper 



a ui 



Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 

Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 
Calcomp 



□ wo * PART No, BKV SERIAt. HO. 



20001' 
10812' 
10814- 
10816- 
10818- 
10820- 
10822- 
20438- 
10826- 
10828- 
10830- 
10832- 
10003- 
10003- 



•102-301 

•502-000 

•502-111 

•502-000 

502-201 

■502-000 

■502-000 

■502-000 

502-000 

502-000 

502-201 

502-101 

502 

502 



20002-102 

10326-502-100 

10323-502-000 

10323-502-000 

10326-502-100 

20431-502-000 

10323-502-000 

10326-502-100 

20431-502-000 

10475-502-000 

10326-502-100 

10323-502-000 

10323-502-000 

10111-401-000 

10111-401-000 

10111-401-000 

10110-401-000 

10110-401-000 

10110-401-000 

10110-401-000 

10146-401-000 

10269-401-000 

10269-401-000 

20205-401-000 

20205-401-000 



None 

3 

7 

3 

None 

4 

1 

1 

4 

5 

None 

6 



1 

3 

3 

3 

3 

1 

3 

3 

1 

2 

3 

3 

3 

4 

4 

4 

2 

2 

2 

2 

3 

5 

5 

None 

None 



.EAB-FT2 
F013 
F013 
F015 
F013 
F013 
F013 
F013 
F013 
F013 
F014 
F013 
F016 
F015 

EAB-FT2 

F30il 

F3011 

F3012 

F3012 

F3004 

F3013 

F3014 

F3006 

F3006 

F3015 

F3015 

F3014 

F3007 

F3008 

F3009 

F3012 

F3006 

F3007 

F3005 

F3002 

F3006 

F3005 

F3006 

F3005 



Page 15 

A-27 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



NOMKMCt.ATuRC 


auppt.1 K R 


OWO • FART NO 


RKV 


•CR 1 AL HO. 


Attitude Control System 


GE-SS 


47E213514G2 


AN- 10 


114 


Telemetry Conversion Module 


GE-SS . 


238R405G2 




6549356 


Structure /Thermal Subsystem 


FHC 


831-11-1000-1 


A 


FT4 


Louver, Ht. Shld, & Supt. 


FHC 


831-11-0300-11 


D 


6 


Louver Support Assembly 


FHC 


831-11-0301-21 


G 


6 


Heat Shield Assembly 


FHC 


831-11-0306-31 


K 


6 


Louver Assembly 


FHC 


831-11-0120-31 


B 


6 


Temperature Sensing Inst. 


FHC 


831-11-0142-21 


G 


6 


Albedo Shield, Left 


FHC 


831-11-0210-61 


C 


6 


Albedo Shield, Right 


FHC 


831-11-0210-62 


C 


6 


Temperitture Sensing Inst. 


FHC 


831-11-0142-31 


G 


6 


Pitch Reaction Wheel 


Bendix 


X1903155-2 


D 


EAB-FT-02R 


Wheel, Hub, & Rotor Ass'y. 


Bendix 


X1875403-1 


A 


202 


Shaft & Stator Assembly 


Bendix 


X1875402-1 


B 


203 


Shaft, Final Machining 


Bendix 


X1875404-1 


B 


203 


Motor Rotor 


Bendix 


X1877013-1 


A 


208 


Motor Stator 


Bend ix 


X1877036-1 


C 


7107003 


Yaw Reaction V^/heel 


Bendix 


X1898720-2 


D 


EAB-FT-02R 


Flywheel & Rotor Assembly 


Bendix 


X1898721-1 


C 


202 


Housing & Closure Mach.Asy. 


Bendix 


X1891422-1 


C 


201 


Motor Stator 


Bendix 


X1877036-1 


C 


7107002 


Hearing Sleeve 


Bendix 


X1898717-1 


A 


202 


Shouldered Shaft 


Bendix 


X1898730-1 


B 


202 


Labyrinth Seal 


Bendix 


X1898728-1 


None 


204 


Locking Ring 


Bendix 


X1898729-1 


B 


202 


Control Logic Box 


Ithaco 


D40778G2 


C 


FT- 10 


Al Card 


Ithaco 


D40721G1 


D 


11619 


A2 Card 


Ithaco 


D40752G1 


C 


11621 


A3 Card 


Ithaco 


D40753G1 


C 


11622 


A4 Card 


Ithaco 


D4075AG1 


C 


15036 


A5 Card 


Ithaco 


D40755G1 


D 


11626 


A6 Card 


Ithaco 


D40253G2 


D 


11615 


A7 Card 


Ithaco 


D40253G2 


D 


11616 


A8 Card 


Ithaco 


D40728G1 


D 


11628 


A9 Card 


Ithaco 


D40179G2 


F 


11524 


RRWS/Signal Processor Asy. #1 


Ithaco 


D40770G3 


D 


FT- 14 


Signal Processor 


Ithaco 


D40769G3 


B 


11629 


Al Card 


Ithaco 


C30302G2 


I 


11676 


A2 Card 


Ithaco 


C31066G1 


C 


11659 


A.\ Card 


Ithaco 


C31167G1 


B 


11669 


Roll Reaction Wheel Scanner 


Bendix 


X1871380-2 







Page 16 



A-28 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



N O M ■ M C U A T U H E 


9UPPI.IK R 


DWO Ji PART NO, 


SKV 


• K R lAl. NO. 


Attitude Control System (cent) 




■ 






RRWS/Signal Processor Asy.#2 


Ithaco 


D40770G4 


D 


FT- 15 


Signal Processor 


ithaco 


D40769G4 


B 


11640 


Al Card 


1 thaco 


C303O2G2 


I 


11677 


A2 Card 


Ithaco 


C31066G1 


C 


11660 


A3 Card 


Ithaco 


C31167G1 


B 


11670 


Roll Reaction Wheel Scanner 


Bendix 


X1871380-2 






Pneumatics Subsystem 


'mj 


113580 


El 


008 


Solenoid Valves 










+ Pitch 




PT2-3030-1 


G 


17 


' Pitch 




Fr2- 3030-1 


G 


18 


+ Roll 




PT2-3b30 


G 


33 


- Roll 




PT2-3030 


G 


24 


+ Yaw 




PT2-3030 


G 


34 


- Yaw 




Fl'2-3030 


G 


32 


Supt. Nozzle L'ube Assemblies 










+ Yaw 




116599-5 


C 


074 


- Yaw 




116599-6 


C 


076 


+ Yaw 




113586-5 


C 


069 


- Yaw 




113586-6 


C 


072 


Nozzles 










+ Pitch 




113591-3 


B 


Oil 


- Pitch 




113591-3 


B 


013 


+ Roll 




113593-3 


B4 


014 


- Roll 




113593-3 


B4 


025 


+ Yaw 




113593-3 


B4 


018 


- Yaw 




113593-3 


B4 


016 


+ Yaw 




113593-3 


B4 


020 


- Yaw 




113593-3 


B4 


023 


Regulator 




FL'2-3032 


E 


05 


I,ow Pressure I'ransduL ir 




Fr2-3068 


C 


88 


lligli Pressure Transclucor 




Pr2- 3033-1 


F 


1004 


(las Tempera tuTL' Transiiuf*.' r 




l'T2-3083 


B 


0004 


Manifold Temp. Transduct'r 




I>t:'-303 5-2 


V 


0004 


J'ressure Vessel 




i:i l34.'.l-2 


A4 


12 


I'iU Valve 




(;2632 56-] 


El 


28485-2 


Manii'old 




11358:^3 


Fl 


008 


Mounting Plattorm 




1 13581- 7 


E2 


008 


LLPS Filter 




(:120031-1 


None 


008 


Junction Box 




23358G-5 


D3 


008 


Initiation Timer 


GE-SS 


47E221985G1 


AN- 9 


6549484 



0BIGINAL ?4§i f§ 
OF POOR QUALrE? 



Page 17 

A-29 



CONSOLrOATED CONFIGURED ARTrCLES LIST 



ERTS SPACECRAFT 903 



MOMCMCUATUVtE 

Attitude Control System (contO 




OWO 4b ^ A ft T HOI 


»« V 


• CfflAL M<^ 


Solar Array Drive, RH 


TRW 


E2A6623-7 




FT04 


Al Electronics 




E235406-4 


J3 


FTOl 


A2 Electronics 




E235397-4 


G2 


FTOl 


V^abble Gear 




233773-3 


E5 


FT06 


Motor 




264666 . 


A2^v 


13, 23 


Sun Sensor 




E242143-i 


C2 


FT23, FT24 


Voltage Regulator 




E250692-1 


D2 


FT 08 


Transducer 




PT2-3039 


c 


1009 
684891 


Potentiometer 




PT2-3040 


A 


Slip Ring 




C232457-1 


Bl 


9 


Solar Array Drive, LH 


TRW 


E246623-7 




FT-005F 


Al Electronics 




E235406-4 


J3 


005 


A2 Electronics 




E235397-4 


G2 


005F 


Wabble Gear 




233773-3 


E5 


R005 


Motor 




264666 


A2 


4 


Sun Sensor 




E242143-1 


B5 


003F,004F 


Voltage Regulator 




E250692-1 


A 


005 


Transducer 




Pr2 -3039 


c 


1016 
216583 


Potentiometer 




PT^2-3040 


A 


Slip Ring 




C232457-1 


Bl 


008 


Rate Measuring Package A 


Sperry 


4310-90641-905 


G 


FT08 


Rate Loop Elect, Card 


Sperry 


4216-67676 


F 


13 

20 


Power Conditioning Card 


Sperry 


4331-91544 


A 


Heater Controller Card 


Sperry 


4216-67678 


K 


13 


Telem. Sig. Cond . Card 


Sperry 


4216-67679 


I 


15 


Relay Card A 


Sperry 


4331-91545 


None 


20 


Relay Card B 


Sperry 


4216-67681 


C 


20 


Inverter Subassembly 


Sperry 


4331-91579 


None 


16 


RFI Assembly 


Sperry 


4310-90627 


C 


15 


RNP Cable Harness 


Sperry 


4216-90956-2 


F 


15 


Cyro, Rate Integrating 


Northrop 


P/N 67516 


None 


N8 


Normalization Assembly 


Sperry 


4331-91578 


None 


18 


Rate Measuring Packagu 13 


Sperry 


4310-90641-W3 


E 


NIM-D-FT03 


Rate Loop Klod. Card 


Spt^rry 


4216-67576 


E 


GA 


Power Conditioning Card 


Sporry 


4216-67677 


F 


6A 


Heater Controller c:ard 


Sperry 


4216-67678 


J 


6A 


Telem, Sig. Cond. Card 


Sperry 


4216-67679 


G 


6A 


Relay Card A 


Sperry 


4310-90848 


None 


6A 


Relay Card fi 


Sperry 


4310-90841 


A 


6A 


Inverter Subassembly 


Spurry 


4310-90633 


F 


6A 


RFT Assembly 


Sperry 


4310-90627 


M. 

A 


6A 


RMP Cable Harness 


Sperry 


4216-90956-2 


D 


6A 


Cyro. Rate Integrating 


Sperry 


1200941 


n 


n 


Normalization Assembly 


Sperry 


4310-90843 




n 














E,0, Al Not Incorporated 



Page 18 



A-30 



CONSOLIDATED CONFIGURED ARTICLES LIST 

ERTS SPACECRAFT 903 



NUMKHCLATitnC 



«UI 



OWO * PART MO, RKV 



• ■ R I At. MO. 



Attitude Control System (cont) 

Yaw Rate Gyro 
Choke, Module 
Transformer, Module 
Thermistor, Module 
Gyroscope, Rate 
P.C. Component Board 
F.C. Component Board 
P.C. Component Board 
P.C. Component Board 
Package Assembly 
Component Board 



Paddle Damper, RH 
Paddle Damper, LH 



Wideband Antenna #1 
Wideband Antenna #2 
DCS Antenna 
Command Antenna 
S~Band Antenna 

Quadraloop Antenna #1 

#2 
#3 
#4 



Northrop 



GE-SS 
GE-SS 



GE-SS 

GE-SS 

GE-SS 

GE-SS 

GE-SS 

GE-SS 
GE-SS 
GE-SS 
GE-SS 



63861-302 
63880-301 
63881-301 
63866-302 
79142-301 
63876-302 
63877-302 
63878-302 
63879-302 
63843-302 
63844-302 



248E126G4 
248EI26G4 



47D222340G1 

47D222340G1 

47D210564G3 

113C7468G1 

111C2955G5 

248E754G8 
248E754G8 
248E754G8 
248E754G8 



J 


FT3 


C 


102 


C 


102 


E 


104 


E 


D-975 


H 


N3 


G 


N3 


J 


N3 


H 


N3 


M 


NEF/EAB-FT3 


E 


m 



AN -19 
AN -19 



-4 

-4 

-6 

-3 

-8 

-6 
-6 
-6 
-6 



6549641 
6549642 



6549589 

6549588 

6549518 

6549515 

6549365 

6549494 
6549495 
6549496 
6549497 



Page 19 
Revision B 



A-31 



CONSOLIDATED CONFIGURED ARTICLES LIST 



ERTS SPACECRAFT 903 



NOMKHCLATunE 



VHF TRANSMITTER 

Electrical Assembly 
RF Transmitter Assenbly 

Oscillator/Buffer Al 

Phase Modulator A2 

Limlter Tripler A3 

Driver Amplifier A4 

300 MV Amplifier A5 

2 W Amplifier A6 

Output Filter A7 

Oscillator/Buffer A8 

Phase Modulator A9 

Limlter Tripler AID 

Driver Amplifier All 

300 MV Amplifier A12 

2 W Amplifier A13 

Output Filter A14 

Isolator A15 
Power Reg. Elec. Assembly 
Power Regulator 
Filter Modulator 



RADIATION 



»vm^ L I c I 



Owo > l»AWT MO BKV ■•■RIAL N 



6i3202Gl 

61320501 

613203G1 

5296 llGl 

529738G1 

529612G1 

418053G1 

52960901 

5296 lOGl 

41805401 

529611G1 

529738G1 

529612G1 

418053G1 

529609G1 

5296 lOGl 

418054G1 

115479-102 

613209G1 

5296 15G1 

529732G1 



Al 

None 

B2 

A5 

A2 

A7 

A7 

A5 

A7 

A4 

AS 

A2 

A7 

A7 

A5 

A7 

A4 

NA 

A 

A2 

A2 



FT0004 
0003 
0003 
0004 
0003 
0004 
0007 
0007 
0005 
0008 
0006 
0006 
0007 
0008 
0008 
0009 
0007 
10 
0003 
0004 
0003 



GOVERMMEMT FURNISHED EQUIPMENT 



Return Beam Vidlcon 

Camera Sensor (Blue) #2 
Camera Sensor (Yellow) #1 
Camera Sensor (Red) #3 
Camera Cont. /Combiner 
Camera Electronics #1 
Camera Electronics #2 
Camera Electronics #3 

Wide Band Video Tape Recorder 
Transport Unit 1 
Transport Unit 2 
Electronics Unit 1 
Electronics Unit 2 

Multi Spectral Scanner System 
Multiplexer 
Scanner 
MSS Line Filter 

ECAM 



RCA 
RCA 
RCA 
RCA 
RCA 
RCA 
RCA 
RCA 

RCA 
RCA 
RCA 
RCA 
RCA 

Hughes 
Hughes 
(SBRC) 
Hughes 

GSFC 



2265041-501 
1976477-501 
1976477-502 
1976477-503 
2265336-501 
1976466-501 
1976466-501 
1976466-501 

202835-001 

8358497-501 

8358497-501 

8370323-501 

8370323-501 

3241000-100 
3241140-100 
43727 
3241160-100 

GF1308902 



004 
003 
008 
003 
003 
004 
008 



FLT2 
FLT6 
FLT2 
FLT6 

002 . 
001 

002 
004 

P-FLT 



I 



A^32 



Page 20 
Rev. B 



APPENDIX B 
COMMAND MATRIX 





Table B-1. 


LANDSAT-2 


CMD# 


Command Function 


CMD# 


000 


Spare (Clock) 


035 


001 


Pri COMSTOR On & Fill 


036 


002 


Spare (Clock) 


037 


003 


Pri COMSTOR Verify 


040 


004 


Pri COMSTOR Copy 


041 


005 


Pri COMSTOR Off 


042 


006 


Pri COMSTOR Activate 


043 


007 


Serial Data Transfer On 


044 


010 


CMD Execution Counter Reset 


045 


Oil 


Select Pri Matrix Decoder 


046 


012 


Select Pri Matrix A Drivers 


047 


013 


Select Pri Matrix B Drivers 


050 


014 


Select Pri Oscillator 


051 


015 


Select Pri Freq, Generator 


052 


016 


Spare (Clock) 


053 


017 


Load Time Code 


054 


020 


Non-Keyed PS/COMDECS Off 


055 


021 


Red COMSTOR On & Fill 


056 


022 


Spare (Clock) 


057 


023 


Red COMSTOR Verify 


060 


024 


Red COMSTOR Copy 


061 


025 


Red COMSTOR Off 


062 


026 


Red COMSTOR Activate 


063 


027 


Spare (Clock) 


064 


030 


Spare (Clock) 


065 


031 


Select Red Matrix Decoder 


066 


032 


Select Red Matrix A Drivers 


067 


033 


Select Red Matrix B Drivers 


070 


034 


Select Red Oscillator 


071 



CMD # Command Function 

Select Red Freq. Generator 

Spare (Clock) 

Spare (Clock) 

Pneumatics Enable 

0, 3^ Yaw Position Bias Enable 

Pneu Interlock Bypass Disable 

Spare 

Pneu Low Voltage Biter lock Reset 

Differential Tach Disable 

WBPA 2 Power On 

WBPA 2 Select lOW Output 

APU Standby Mode 

EC AM Load 

MSS System On 

MSS Select Inverter A 

MSS Select Band 1 High Voltage A 

MSS Select Band 2 High Voltage A 

MSS Select Band 3 High Voltage A 

MSS Band 1 On 

0. 30 Yaw Position Bias Disable 

Pneumatics Disable 

Spare 

Pneu Interlock Bj^ass Enable 

Differential Tach Enable 

EC AM Execute 

Spare 

WBPA 2 Power Off 

Spare 

APU Normal Mode 



B-1 



Table B-1. LANDSAT-2 Commands (Cont'd) 



CMP # Command Function 

072 MSS Select Inverter B 

073 MSS System Off 

074 MSS Select Band 2 High Voltage B 

075 MSS Select Band 1 High Voltage B 

076 MSS Band 1 Off 

077 MSS Select Band 3 High Voltage B 

100 Differential Tach Normal Gain 

101 0. 1° Yaw Position Bias Enable 

102 RLNA into Yaw Disable 

103 2. 9° Pitch Position Bias Enable 

104 Pitch Momentum Bias Disable 

105 ECAM Hun A 

106 WBPA 2 Select 20W Output 

107 USB Bypass Aux Oscillator 

110 USB Select Transmitter B 

111 Spare 

112 MSS High Voltage On 

113 MSS Band 2 On 

114 MSS Band 3 On 

115 MSS Band 4 On 

116 Spare (MSS) 

117 MSS Select Calibration Lamp A 

120 0. 1° Yaw Position Bias Disable 

121 Differential Tach High Gain 

122 2. 90 Pitch Position Bias Disable 

123 RLNA into Yaw Enable 

124 Negative Pitch Position Bias 

125 Pitch Momentum Bias Enable 

126 USB Select Transmitter A 



CMD# Command Function 

127 USB Ranging On 

130 USB Modulation Input Crossed 

131 Spare 

132 MSS Band 2 Off 

133 Spare (MSS) 

134 MSS Band 4 Off 

135 MSS Band 3 Off 

136 MSS Select Calibration Lamp B 

137 Spare (MSS) 

140 Roll Unload Disable 

141 Negative Yaw Position Bias 

142 Yaw Wheel Disable 

143 Spare 

144 Pitch Unload Disable 

145 Positive Pitch Position Bias 

146 USB Ranging Off 

147 USB Modulation Input Normal 

150 USB Enable Aux Oscillator 

151 Spare 

152 MSS Rotating Shutter Driver On 

153 MSS Scan Monitor On 

154 MSS Band 1 High Gain 

155 MSS Band 2 High Gain 

156 MSS Calibration Lamp On 

157 MSS Band 1 High Voltage On 

160 Positive Yaw Position Bias 

161 Roll Unload Enable 

162 Pneumatics Momentary Enable 

163 Yaw Wheel Enable 



B-2 



Table B-1. LANDSAT-2 Commands (Cont'd) 



CMD# Commajgd Fujiction 

164 ECAM Run B 

165 Pitch Unload Enable 

166 VHP Xmtr Playback Mode 2 

167 VHF Xmtr Power 1 Off 

170 VHF Xmtr Power 2 On 

171 VHF Xmtr Playback Override Off 

172 MSS Scan Monitor Off 

173 MSS Rotating Shutter Driver Off 

174 MSS Band 2 Low Gain 

175 MSS Band 1 Low Gain 

176 MSS Band 1 High Voltage Off 

177 MSS Calibration Lamp Off 

200 Orbit Adjust Mode Enable 

201 ECAM On 

202 Rate Measuring Package A Enable 

203 400 RPM Interlock Enable 

204 Yaw Acquisition Mode 

205 Spare 

206 VHF Xmtr Power 1 On 

207 VHF Xmtr Realtime Mode 

210 VHF Xmtr Low Power Mode 

211 VHF Xmtr Power 2 Off 

212 MSS Band 2 High Voltage On 

213 MSS Band 3 High Voltage On 

214 MSS Sel Shutter Monitor Source A 

215 Spare (MSS) 

216 Spare (MSS) 

217 MSS Scanner Power Line 1 

220 ECAM Off 

221 Orbit Adjust Mode Disable 



CMD # Command Function 



222 


400 RPM Interlock Disable 


223 


Rate Measuring Package B Enable 


224 


Spare 


225 


Yaw Normal Mode 


226 


Spare 


227 


VHF Xmtr High Power Mode 


230 


VHF Xmtr Playback Override On 


231 


VHF Select Xmtr A 


232 


MSS Band 3 High Voltage Off 


233 


MSS Band 2 High Voltage Off 


234 


Spare (MSS) 


235 


MSS Sel Shutter Monitor Source B 


236 


MSS Scanner Power Line 2 


237 


Spare (MSS) 


! 240 


TMP Select Memory Unit A 


241 


Spare 


242 


TMP Select Memory Sequencer A 


243 


Spare 


244 


Left SAD Normal Rate . 


245 


ECAM Zero Time 


^'' 246 


Battery 1 Off 


247 


Rate Measuring Package B Htr Off 


250 


VHF Select Xmtr B 


251 


VHF Xmtr Playback Mode 1 


252 


Spare (MSS) 


253 


Spare (MSS) 


254 


Spare (MSS) 


255 


MSS Select Scan Monitor Source A 


256 


MSS Scan Mirror Inhibit 


257 


MSS Mux Normal 



B-3 



Table B-1. LANDSAT-2 Commands (Cont'd) 



CMD # Command Function 



260 


TMP Select A/D Converter A 


315 


261 


TMP Select Memory Unit B 


316 


262 


TMP Select Analog Mux A 


317 


263 


TMP Select Memory Sequencer B 


320 


264 


Battery 5 Off 


321 


265 


Battery 6 Off 


322 


266 


Rate Measuring Package B Off 


323 


267 


Battery 2 Off 


324 


270 


Right Sad Disable 


325 


271 


BMP A Motor Start 


326 


272 


Spare (MSS) 


327 


273 


Spare (MSS) 


330 


274 


MSS Select Scan Monitor Source B 


331 


275 


Spare (MSS) 


332 


276 


MSS Mux Inhibit 


333 


277 


MSS Scan Mirror Normal 


334 


300 


TMP Select Digital Mux A 


335 


301 


TMP Select A/D Converter B 


336 


302 


TMP Select Formatter Logic A 


337 


303 


TMP Select Analog Mux B 


340 


304 


Rate Measutring Package B Mtr On 


341 


305 


BMP B Heater & Electronics On 


342 


306 


Battery 7 Off 


343 


307 


Rate Measuring Package A Off 


344 


310 


Battery 3 Off 


345 


311 


Right Sad Enable 


346 


312 


MSS Scan Mirror Power Line 1 


347 


313 


Spare (MSS) 


350 


314 


MSS Mid Scan Code On 


351 



CMD # Command Function 

MSS Mux Compression Mode 

MSS System ON/OFF Normal 

Spare (MSS) 

Spare 

TMP Select Digital Mux B 

Spare 

TMP Select Formatter Logic B 

ECAM Output Enable 

Left SAD High Rate 

RMP AQn 

Battery 8 Off 

RMP B Lower Motor Voltage 

Battery 4 Off 

Spare (MSS) 

MSS Mux Linear Mode 

Spare (MSS) 

MSS Mid Scan Code Off 

MSS Scan Mirror Power Line 2 

MSS System ON/OFF Override 

TMP Memory Write On 

TMP Matrix Verify Override On 

TMP No Mod to VHF Override On 

TMP Program Control Bit Off 

Left SAD Disable 

Spare 8 Set 

Trickle Charge Normal 

Enable USBX Off 

DCS Receiver 2 On 

RBV Primary Control Enable 



B-4 



CMD# 

352 

353 

354 

355 

356 

357 

360 

361 

362 

363 

364 

365 

366 

367 

370 

371 

372 

373 

374 

375 

376 

377 

400 

401 

402 

403 

404 

405 

406 



Table B-1. LANDSAT-2 Commands (Cont'd) 

# Command Function 
DCS Receiver 1 Off 



Command Function 


CMD# 


RBV Cathode Reactivation On 


407 


All Batteries On 


410 


Shunt Load A Off 




All Comp Loads Off 


411 


Aux Load 1 On 


412 


Aux Load 2 On 


413 


Spare 8 Reset 


414 


TMP Memory Write Off 


415 


TMP Program Control Bit On 


416 


TMP Program Control Bit 1 On 


417 


Disable USBX Off 


420 


Left SAD Tenable 


421 


DCS Receiver 1 On 


422 


Trickle Charge Override 


423 


Rate Measuring Package A Htr On 


424 


RBV Cathode Reactivation Off 


425 


RBV Enable Calibration 


426 


Verify Tick 


427 


AU Aux Loads Off (A) 


430 


Shunt Load B Off 


431 


Comp Load 1 On 


432 


Comp Load 2 On 


433 


TMP Data to VHF Xmtr 


434 


TMP Program Control Bit 1 Off 


435 


TMP Matrix Verify Override Off 


436 


TMP Verify Memory On 


437 


Right SAD High Rate 


440 


RBV Camera 3 On 


441 


DCS Receiver 2 Off 


442 



Rat e Measuring Package A Lower 
Motor Voltage 

RBV/CCC Power On 

RBV Aperture Corrector In 

All Aux Loads Off (B) 

Comp Load 3 On 

Shunt Load C Off 

Comp Load 4 On 

Comp Load 5 On 

TMP No Mod to Override Off 

TMP No Mod to VHF Xmtr 

TMP Verify Memory Off 

Spare 

RBV Primary Control Disable 

Right SAD Normal Rate 

WBVTR 1 Record 

RBV Single Cycle 

RBV Start Prepare 

RBV Aperature Corrector Out 

RBV CCC Power Off 

RBV Camera 1 On 

Comp Load 6 On 

Aux Load 3 On 

Aux Load 4 On 

All Shunt Loads On 

TMP Select Xmtr Buffer AMP A 

TMP Matrix Verify On 

TMP Power 2 Off 



B-5 



CMD# 

443 

444 

445 

446 

447 

450 

451 

452 

453 

454 

455 

456 

457 

460 

461 

462 

463 

464 

465 

466 

467 

470 

471 

472 

473 

474 

475 

476 

477 



Table B-1. LANDSAT-2 Commands (Cont'd) 
Command Function CMP # Command Function 

TMP Force Program 00 Off 500 TMP Memory Write/Verify Ovrd On 

WBVTR 1 Volt Protect Relay Reset 501 
WBVTR 1 Record Current Adjust 502 



WBVTR 1 RBV Enable 

WBVTR 1 Playback 

RBV Exposure 1 

RBV Exposure 2 

RBV Exposure 5 

RBV Exposure 3 

RBV Exposure 4 

Aux Load 5 On 

Shunt Load D Off 

Verify Took 

TMP Pre-Regulator A On 

TMP Select Xmtr Buffer AMP B 

TMP Force Program 00 On 

TMP Pre-Regulator Output A 

WBVTR 1 RBV Standby 

WBVTR 1 Fast Rewind 
WBFM Select VCO Bl 

WBVTR 1 Voltage Protect Enable 
RBV Continuous Cycle 
RBV Camera 2 On 
RBV Start Calibrate 
RBV Disable Calibrate 
Aux Data to RBV Filter A 
RT 1 Data to MSS Filter B 
RT Data to RBV Fitter B 
Enable RBV Filter B 



TMP Pre-Regulator Output B 
TMP Matrix Normal 

503 TMP Power 1 Off 

504 WBVTR 1 Fast Forward 

505 WBVTR 1 MSS Standby 

506 WBVTR 1 Voltage Protect Disable 

507 WBVTR 1 Lap 

510 RBV Camera 2 Off 

511 RBV Camera 1 Off 

512 RBV Camera 3 Off 

513 WBVTR 2 Record 

514 RT 1 Data to MSS Filter A 

515 RT Data to RBV Filter A 

516 RT 2 Data to MSS Filter B 

517 WBVTR 1 Data to RBV FUter B 

520 TMP Power 2 On 

521 TMP Memory Write/Verify Ovrd Off 

522 TMP Power 1 On 

523 TMP Pre-Regulator B On 

524 WBFM Select VCO Al 

525 WBFM Inverter A Power On 

526 WBFM Enable Modulator A AFC 

527 WBFM Inverter B Power Off 

530 WBFM Disable Modulator B AFC 

531 WBVTR 2 Data to RBV Fitt er B 

532 WBVTR 2 Record Current Adjust 

533 WBVTR 2 RBV Enable 

534 WBVTR 2 Playback 



B-6 



Table B-1. LANDSAT-2 Commands (Cont'd) 



CMD# 


Command Function 


CMD# 


535 


RT 2 Data to MSS Filter A 


572 


536 


WBVTR 1 Data to RBV Filter A 


573 


537 


WBVTR 1 Data to MSS Filter B 


574 


540 


WBPA 1 Power On 


575 


541 


WBPA 1 Select lOW Output 


576 


542 


NBTR 2 Playback Mode 


577 


543 


NB'm 1 Record Mode 


600 


544 


Enable RBV Filter A 


601 


545 


WBFM Disable Modulator A AFC 


602 


546 


Select RBV Bias A 


603 


547 


WBFM Select VCO A2 


604 


550 


WBFM Inverter B Power On 


605 


551 


WBVTR 2 RBV Standby 


606 


552 


WBVTR 2 Fast Rewind 


607 


553 


WBVTR 2 Voltage Protect Relay 


610 




Reset 


611 


554 


WBVTR 2 Voltage Protect Enable 


612 


555 


Enable MSS Filter A 




556 


WBVTR 1 Data to MSS Filter A 


613 


557 


WBVTR 2 Data to RBV Filter A 


614 


560 


Orbit Adjust Timer Enable 


615 


561 


WBPA 1 Power Off 


616 


562 


NBTR 1 Power Off 


617 


563 


WBVTR Search Track Switched 


620 


564 


Select RBV Bias B 


621 


565 


WBFM Select VCO B2 


622 


566 


WBFM Inverter A Power Off 


623 


567 


WBFM Enable Modulator B AFC 


624 


570 


WBVTR 2 Data to MSS FUter B 


625 


571 


WBVTR 2 Fast Forward 


626 



CMD # Command Function 

WBVTR 2 MSS Standby 

WBVTR 2 Voltage Protect Disable 

WBVTR 2 Lap 

Aux Data t o RBV Filter B 

Enable MSS Filter B 

WBVTR 2 Data to MSS Filter A 

WBPA 1 Select 20W Output 

NBTR 2 Record Mode 

0. 6°Yaw Position Bias Enable 

Orbit Adjust Timer Disable 

Select NBTR 2 

PMP Modulator A On 

Select NBTR 

WBVTR 1 On (Primary) 

MSS Enable (Primary) 

Spare 

RBV No. 1 Thermoelectric Module 
Disable 

ISM Disable Selected Scanner 

ISM Switched Telemetry Power On 

Orbit Adjust Thruster Heater On 

MSFN to ClU A/STADAN to CIU B 

Disable PSM Relay Buss 

NBTR 2 Power Off 

NBTR 1 Playback Mode 

Payload Reg Module Fuse Tap On 

0. 6° Yaw Position Bias Disable 

Select WBVTR 1 

Inhibit WBFM RBV/A MSS B Filters 

PMP Modulator A Off 



B-7 



CMD # Command Function 



Table B-1, LANDSAT-2 Commands (Cont'd) 

CMD # Command Function 



627 Orbit Adjust On 1 

630 WBVTR 1 Control Normal 

631 WBVTR Search Track Normal 

632 MSS Enable (Both) 

633 Right SAD Unfused 

634 CMD Clock Relays on 5A Fuse 

635 ISM Separation Switch Bypass 

636 ISM Enable Scan & Select A 

637 ECAM Smart Disable 

640 2. QO Pitch Position Bias Enable 

641 PSM Inverter A Power to WBFM 

642 0. 6° Pitch Position Bias Enable 

643 WBVTR 1 Control Reversed 

644 PMP Modulator B On 

645 Select WBVTR 2 

646 Select NBTR 1 

647 MSS Disable 

650 WBVTR 2 On (Primary) 

651 WBVTR 1 Off 

652 Spare 1 (Non- Latch) 

653 CMD Clock Relays on lA Fuse 

654 Left SAD Unfused 

655 Enable PSM Relay Bus 

656 APU Power On 

657 Orbit Adjust Thruster Heater Off 

660 PSM Inverter B Power to WBFM 

661 2. 0° Pitch Position Bias Disable 

662 MSS Enable (Redundant) 

663 0. 6° Pitch Position Bias Disable 



664 PMP Select WBVTR 

665 PMP Modulator B Off 

666 Inhibit WBFM RBV B/MSS A Filters 

667 RBV On (Primary) 

670 PSM Solenoid 1 On 

671 WBVTR 2 Control Normal 

672 RBV No. 3 Thermoelectric Module Ena 

673 ISM Switched Telemetry Power Off 

674 Right SAD Fused 

675 Lock Single Scanner Mode 

676 Enable USB Xmtrs (Redundant) 

677 RBV Magnetic Compensator Enable 

700 MMCA Power On 

701 Enable Payload Timer Signal 

702 MMCA Pitch Coil Out 

703 Inhibit Data to RBV Filter A 

704 MMCA Yaw CoU Out 

705 Prime Data to WBPA 1/2 

706 MMCA Capacitor Dump 

707 RBV No. 2 Thermoelectric Module Dis 

710 RBV On (Redundant) 

711 PSM Solenoid 2 On 

712 WBVTR 2 Off 

713 Left SAD FUsed 

714 Unlock Single Scaimer Mode 

715 MSFN to cm B/STADAN to CIU A 

716 Attitude Sensor Power On 

717 Spare (Non- Latch) 

720 Disable Payload Timer Signal 



B-8 



Table B-1. LANDSAT-2 Commands (Cont'd) 



CMD# 


Command Function 


CMD# 


Command Function 


721 


MMCA Pitch Coil In 


755 


Enable USB/WBPA Timer Signal 


722 


Inhibit Data to RBV Filter B 


756 


Comp Load 7 On 


723 


MMCA Yaw Coil In 


757 


Disable USB Xmtrs 


724 


Summed Data to WBPA 1 


760 


Inhibit Data to MSS Filter B 


725 


MMCA Capacitor Charge 


761 


MMCA Roll Coil Out 


726 


WBVTR 2 Control Reverse 


762 


MMCA Capacitor Low 


727 


Payload Reg Module On 


763 


MMCA Polarity Negative 


730 


RBV No. 2 Thermoelectric Module 
Ena 


764 


Orbit Adjust Off 




765 


MMCA Power Off 


731 


RBV Off 










766 


Payloads Off 


732 


PSM Solenoid 3 On 










767 


Payload Reg Module Fuse Tap Off 


733 


Switch Payload Regulator 










770 


RBV No. 1 Thermoelectric Module Ei 


734 


ISM Enable Scan & Select B 






7^^ 


gOjgt 1 S/Hf ^^T £A^/tS^e 


771 


Payload Reg Module Off 2 


f OiJ 




772 


Disable USB/WBPA Timer Signal 


736 


RBV Magnetic Compensator Lo Mode 










773 


Comp Load 8 On 


737 


APU Power Off 










774 


Attitude Sensor Power Off 


740 


MMCA Roll Coil In 










775 


Enable USB Xmtrs (Primary) 


741 


Inhibit Data to MSS Filter A 










776 


Enable WBPA (Primary) 


742 


MMCA Polarity Positive 










777 


Spare 


743 


Summed Data to WBPA 2 










780 


Switch Spacecraft PWM Regualtor 


744 


MMCA Capacitor High 










781 


CIU Channel B Off 


745 


PSM Solenoids Off 










782 


CEJ Ch B Qn/Sw STDN/MSFN Cmd 


746 


Orbit Adjust On 2 




Link 


747 


RBV On Both 


783 


CMD Clock Pwr Supply/Comdecs On/ 


750 


Payload Reg Module Off 1 




ECAM Output Disable 


751 


RBV No. 3 Thermoelectric Module 


784 


Switch £i)acecraft PWM Regulator 




Dis 


785 


CKJ Channel A Off 


752 


RBV Magnetic Compensator Disable 


786 


CIU Ch A Qn/Sw STDN/MSFN Cmd 


753 


RBV Magnet ic Compensat or Hi Mode 




Link 


754 


Enable WBPA (Redundant) 


787 


CMD Clock Pwr Supply/Comdecs On/ 



ECAM Output Disable 



B-9/10 



J 



Table B«2. LANDSAT-2 Command Matrix 



O 

o 
o 



i 

m 




000 



020 



040 



060 



too 



120 



MQ 



160 



200 



220 



2^0 



260 



000 



SPAR£ 



TURN 

NON-KEVEO 
PS/COMOeC 
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PNEUMATICS 
ENABLE 



ACS ro€0) 

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a SABLE , 

Eli 



ACS fiOQ} 

DrFF 

TACH 

nof^hal 

GAIN , 



ACS 

or 

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BIAS 

DISABLE 



C^O 



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ACS 040f) 

ROLL 

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DISABLE 

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ACS (I60i 

POSITIVE 

YAWPOS 

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ACS <^0(A 

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££iM^*A*» 






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SELECT 

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Tm_P C60) 



300 



320 



340 



360 



400 



420 



440 



460 



o 



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500 



520 



MO 



560 



600 



620 



640 



660 



700 



720 



§ 



740 



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760 



TMP C30Q> 

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MEMORy 

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CIQCH QPOO 
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ACS OC 

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TMP (440) 

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TMP fSOO) 
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TMP HOO 
PROGRAM 
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TMP W40 
MATRtX 
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TMP (ioU 

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TMP (SiD 
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W6PAl t54i> 
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10 WATT 
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NBTR2 Cfcoi) 

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MMCA 0*0 

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COIL 



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ACS to4^ 

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ACS <I0?1 
RLNA 
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ACS (122) 

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ACS tM2) 
YAW 

WHEEL 
DISABLE 

GH 



ACS (16?) 
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ACS (ZOZ) 

RMPA 
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ACS (?ia) 

400 RPM 

INTERLOCK 

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TMP (f42J 
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TMP ub2) 
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TMP iZh2) 
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ACS (taa 

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ACS fies) 

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ACS (223) 

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IMP U6« 
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TMP CMil 
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AC^ (0t4> 

0(FF 
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ACS 0041 

PITCH 

MOMENTUM 

BIAS MODE 
QISABI 



JH 



A^ (IZ4) 
NEGATIVE 

PITCH 
POSITION 
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DISABLE 



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ACS (?04) 
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ACQUISTION 
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psmEE^**: 

BATTERY 

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ACS (104) 
RMP B 
MOTOR 
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TMP l4oa 

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TMP we) 
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ryp 144?) TMP C44J) 



POWER 
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IMP 



TMP (463 
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[4431 



TMP &oy 

MATRIX 

NORMAL 

[44 



TMP ^2ti 
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NQTR^MZ} 
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POWER 
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ACS (602) 

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PRM 

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0.to^ 
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PSVJ^ C*4i) 

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TUP (161) 
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TMP W6W 
PRE-RE6 

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TMP (503) 
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WBVTRl fe»il 



FAST 
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ACS ft?3) 

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ACS <66y 

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PSM «»*%> 
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MMCA (T63) 
POLKRITY 
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A(;5 644) 

LEFT 
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p^ij (Shi) 

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USBX 

OFF 

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ACS ^404J 

RIGHT 
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HIGH 
RATE 

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P-5V|(424) 

PRlMflf?y 

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P(?OTECT 

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RBV 
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WBFM^W 



SELECT 

VCO 

AI 



EKIABLE 

R&V 

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5ELECT 

RBV 

BIAS 



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CLOCK< QQS) 
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CLOCK ii>Zt) 

REDUNDANT 

COMSTOR 

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ACS (045) 
DIFF 
TACH 
DISABLE 



ECAM 

EyecuTE 



Rf A/ A 



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ACS 0^5) 
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ENABLE 



AC5 ^2^^^ 

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NORMAL 

MODE 
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eC4A9 
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bATTERV 

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ACS (105) 
RMP B 
HEATER 
^ELEC 
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A£S 0*5) 

LEFT 
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£S£1(34^) 
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006 



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lOOhOOlOPS 



CLOCK <oa^ 

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SELECT 
ZOWATT 
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Ml 



SELECT 
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no 



MODULATION 
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BATTERY 
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ACS OZ6) 
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[30^ 



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ACS 
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ACS C4^b) 

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RATE 



PO^ M^<«.4*3;WfJi 



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PMP <eo4) 

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PMP (e05J 
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PMP (t24l 
SELECT 

WBVTR 

I 

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PMP *<*♦) 

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MMCfc (i44j 
CAP 

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fits 



E5y »i&) 

IHHIBIT 
WBFM 
ftfiV *A5^ D 
HL TERS ■ 



PMp t64&) 

SELECT 

WBVTR 

2 



PMP t***J 
MODULATOR 
B 
OFF 



Pbw (JO*:) 

PRIME 
DATA TO 
W/BPAl/ 



MMCA (nm) 

CAP 

CHARfiE 



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PSM n4«) 
SOLEWQIOS 

OFF 

and 



MMCA (Ifc5) 

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OFF 



Jm 



£^1^044) 

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DCS (366) 
RCVRi 

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Aim 



DCS (406) 
RCVR 2 
OFF 



WBVTRie<2«3 



RECORD 



RBV 
ENABLE 



WBFM (^44) 
SELECT 
VCO 
Bl 



VOLTAGE 

PROTECT 

DISABLE 

Ml 



WBFhA(^«.) 



EM ABLE 
MODULATOR A 
AFC 

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SELECT 
R&V 
8lA^ 
A 



W&FM c»t*) 

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A 

POWER 
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S3S. 
PMP (fcot) 
SELECT 
NBTR 



007 



LOCK (0071 CLOCK WO) 



COMMAItt 
EXECUTION 
COUNTER 
RESET 




CLocKt oar 

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WBRA2 CD47) 
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\0 WATT 
OUTPUT 

M 



WBPA 2 f067^ 

POWER 
OFF 



BYPA55 

AUX 

DSC 



'^ USBXPDfl giOJ 
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XMTR B 



RANQNG 
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VHF^MTR^u:7) 

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xmtr 

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HIGH 

POWER 

MODE 

faio 



ALS 124W 
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HEATER 
OFF 



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&ATTERY 

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OFF 



ACi 
RMP 
OFF 



A 



U£fi„ 



010 



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05C 



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POWER 

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BATTERY 
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SINGLE 

CYCLE 

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WgVTHl(:4475 RBV t4Ka 
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WBVTRl (467] 



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RBV l4?o) 

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CYCLE 



WRVTRi ttO?) 
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WBFM^n) 



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B 

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^BFM (^>'0 
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AFC 



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A 
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OM 

(.Fill WARY) 




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WBFM 
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FILTERS 



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tPRlMARV) 



PiM(^^) 
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PSM (^") 

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LOWER 
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m\ 



DCS (iao) 

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ON 



[406 



ACS 070) 
RMP A 
HEATER 

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ACS t**0) 
RMP A 
LOWER 
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vaTAGE 
[Em 



RBV f430i) 

START 

PREPARE 



RBV tinoi 

CAMERA 

2 

OFF 



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lKlV£ftT£RJ 

& 

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TO MS^ 
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ECAM 
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WOCMAL 
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PLAY&ACit 

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XMTR- 
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PLAYB^VIIC 
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ACS (JiO 

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ENABLE 
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POWER »tfr 



BATTERY 
OFF 



F^M UJI) 

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0(2 



CLOCK <fltf) 
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SELECT 

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DRIVERS , 

-m 



MSS (O&Z) 

SYSTEM 

ON 



MSS (07i) 

SELECT 
INV. B 



MSS 
HIGH 
VOLTAGE 
ON 



(U2) 



MSS (I3£) 

BAND 2 

OFF 

UK 



MSS OMl 
ROTATING 
SHUTTER 
DRIVER 



MSS (iTE) 
SCAN 
MONITOR 
OFF 



M5^ (iiZ) 
BAND 2 
HIGH 
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S teJZ) 
BAND 3 
HIGH 
VOLTAGE 



MSS (ZM) 
DOOR 

wove 



M55 (37^1 
BAKlOSe 

STBP 



MSS (Jli) 
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MIRROR 
POWER 



LINE! 



lu^ 



MSS (332) 

RACHATkDM 

COOLSH 

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RBV 0«) 
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^^Jf^^^J^EACTPATlON 
ENA&LE 



RBV CS7i) 
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OFF 



RBV 
CCC 
POWER 

ON 



(411) 



_|432 



RBV (410 

APERATURE 
CORREaOR 

OUT 



RBV (4in 



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CAMERA 

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RBV (511) 
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PSM (fc»*) 

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PSM (f^»0 
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vssr 



P*iM («»») 
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PSM n^o 

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RBV 
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ViM (nsi*)|PSM 

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JM 



015 



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CLOCK COM) 
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an 



MSS t063) 
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MSS (tJ7S 

SYSTEM 
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losz 



MSS (j(3) 
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MSS 033) 
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MSS 05* 
SCAN 

MONITOR 
ON 
loil 



MSS 073) 
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OFF 



JHl 



MSS (£13) 
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VOLTAGE 
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MSS (^33) 
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MSS (2&3 
B/iHD5A 

StTBP 



M^S (Z73) 

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M£5 0*S 
DOOR 

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MSS (331) 
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MODE 



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ALL 

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RfiV (37^J 
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RBV (412) 
APERATURE 
CORRECTOR 

IN 



RBV (43Zl 
CCC 
POWER 
OFF 

Jiii. 



RBV (45Z) 



EXPoitiTEEl 

5 



RBV (4 7?) 

START 

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RBV (St;) 
CAMERA 

OFF 



WBVTR2 &i 

RECORD 



\ACSi'*,t*f,i*t.f».ifi 



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RBV 

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W&VTZZtiii WBVTR2(ib^ 



FAST 
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MSS 
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PSM (fciJ) 

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TEM 
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I 770 



WBVTRgt?!) WBVTR2 (bNl 



MSS 
ENABLE 
CBOTH) 



PftM C«t> 
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WOM*t*TCH 



RfcV*3 
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PSM C^iaj 
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(1%Z) 

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(St7 




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CLOCK (OM) 
SELECT 
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SELECT 

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M5S t(»4) 

SELECT ■ 

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VOLTAGE 

A 



roT5 



M5^ (D74) 
SELECT 
BAWD ^ 

HIC^H 
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B X^ 



MSS (11^ 
BAND 3 
ON 



MSS C«34) 

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MSS <i** 
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MSS : (Z&<) 



DOOR 

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OKI 



MSS (?») 

SELECT 

5CAU 

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SOURCE 

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MSS 
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CODE 
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OVER RIDE 
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SHUMT 
LOAD 
A 
OFF 



J5il 




PQWERt*^) 

ALL 

AUK 

LOADS 

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RBV (435 

CAMERA 

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RBV C«i 
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3 



RBV C-^'J) 

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5iJ,l^,MI,5«,OT 



VOLTAGE 

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VOLTAGE 
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ENABLE 

[Sri 



VOLTAGE 
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DISABLE 
^f^ 

DISABLE 
SELECTED 

SCANNER 



ISy_<(-'»> 
RiaHT 
SAD 

UNFOSED 
K5± 



ISW (wv») 
CMD CLK 
R£L*(SOM 
lA FUSE 



ISM te7») 

SWITCHED 
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POWER 
OFF 



ISM fri^i 
LEFT 
SAD 
FUSED 



JS 



PSM 0»^^ISM (i^^^l lgM* 

S0LEW(ilO 

ou 



bWlTCH 

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PSM (!»*) 

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HIGH MODE 



ISM 01 W 

COMP 
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a 

OKI- 




las 



RBV (414) 



i^uuja. 



WBFM(*>*j 
AUX 
DATA 
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FILTER A 



WBFM t5*4J 

data' 

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PLAYBACK 



LAP 



ISM f*i4) 
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TELEMETRY 

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CMO CL< 

RELWS OW 
5A FUSE 



ISM (•«) 
LEFT 
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Ml 



RIGHT 
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UNLOCK 

S>^M 



JS2 




EH4&LE 
W6P4 
(KCO) 



ISM (no 
ATTITUDE 
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OFF 



015 



aocK( Oifli 

SELECT 

PRIMARY 

FREQ 

GEfCRATI 



]i 



SELECT 
REDUNDANT 
FREQ 
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MSS '05$ 
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BAWD a 

HIC^H 

VOLTAGE 

^ fQT4 



MSS (or.: 
SELECT 
BAMD I 
HIGH 
VOLTACe 

_&L 1 0S4 



MSS (u^ 

BAND 4 
ON 



MSS (IJM 
BAND 3 
OFF 



MSS OSS 
BAND2 
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GAIN 

Sn±\ 



MSS (17S) 
BAND t 
LOW 
GAIN 

"ill 



MSS (21*) 

OPBKt 
aRECT>OW 

M 



MSS (zia 

SELECT 

SHUTTER 

MOUITDR 

SOURCE 
^ [Hi. 



MSS (255) 

SELECT 

SCAW 

MOMlTOR 

SCMJRCE 

^ kill 



MSS (?7b) 

DOOR 
HOLD 



MS5, iZtb) 

MUX 
COM^HESaC* 
MODE 

Jm 



MSS f33i) 
MID 
SCAN 
CODE 

OFFJiV* 



ALL 
COMP 
LOADS 
OFF, 



POWER& T< POWERCM*) 



SHUWT 
LOAD 

B 



powe£c**> 



SHUKiT 
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c 

OFF. 

iil 



POWER lf**JPOw)ER^i«i 

COMP 

LOAD 

G 

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AUX 
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OM^ 



AUX 
LOAD 
5 
OM , 



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DATA 
TO MSS 
FILTERS 



WBFMft 'i) 
RT DATA 
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FILTER A 

10? 



DATA'' 
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W&FM 6^^3 

EMABLE 

MSS 

FILTER A 



^BFM »t%> 
AUX 
DATA 
TO RBV 
FILTERS 

ISM t<.imi 

ORBIT 

ADJUST 

THRU5TER 

HEATER 

OW 



1651 



SEF>ARiTlOht 

SWITCH 

BVPASS 



ENABLE 

PSM 
l?£LAYfiUS 



LOCK 



ISM oim) 
M5FN TO 

CIU 0/ 
STADW TD 
CtU A 



iito^gBtJJTT 



tCAk\ 
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&IA&CE 



ENABLE 
t^5fl /MT(l/ 

TIMER 



ENABLE 

USfl XMTW 

(PRI> 



016 



aOCK <0i*^ 
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SPARE 



MS5 <o^ 
SELECT 
BAhJD 3 
HIGH 
VOLTAGE 



MSS <^^ 

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OFF 



lOflj 



MSS .^iifc) 

BANJD & 
OW 



MSS (136) 
SELECT , 
CKLlBRATtaU 
LAMP 

a 



MSS <iM^ 
CAU8RATI0N 
LAMP 
ON 



MSS (l?6) 

BANDt 

HIGH 

VOLTAGE 

OFF nsH 



MSS (iie) 
Door 
GVERRiCC 
ACTWATtt 

jm 



MSS '^^^^ 
SCANNER 
POWER 
LINE 2 

04 



MSS iz^e) 
SCAN 
MIRROR 
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ihl 



MSS (Z7tJ 
MUX 

INHIBIT 



MSS L^^6l 
SYSTEM 
ON/OFF 
UORHAL 

{JR. 



SCAN 
MIRROR 
POWER 
LINE 2 \^ 



POMUER &u) 



AUX 

LOAD 

1 



017 



aocK i^n 

LOAD 
TIME 
CODE 



CLQCft ttSft 

smRE 



MSS iOSf) 

BANDt 
ON 



J^ 



MSS *077] 

SELECT 

HIGH 
VOLTAGE 



MSS tuft 

SELECT 
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LAMP 
A 



MSS 037> 

BAKJD S 



MSS U5T> 
BAND t 
HIGH 
VOLTAGE 
ON , — , 



MSS (177) 

CALIBRATIOM 

LAMP 
OFF 



MSS (2175 
SCANNER 
POWER 
LINEI 
n^ 



yss (237) 

DOOR 

MOTOR 

POMCROM 

iinl 



MSS (iW) 
MUX 

NORMAL 

QVw 



MSS C^?0 

SCAN 

MIRROR 

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JM 



MSS (317) 

RAOATlOO 

JIS 



MSS 037) 

SYSTEM 

ON/OFF 
OVEJCRIDE 



pqyia(H*D 

AUX 
LOAD 

0^lm>? 



POWER^lt) 



JaH 



PO^WERO'O 



COMP 
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4 
OM ^ 




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SHUWT 
LOAD 

D 
OFF 



WBFM frTt) 
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FILTER B 



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DATA" 
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W&VTR 1 
DATA 
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FILTER A 



\N&fM(»i 



WBVTR I 
DATA 
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FILTER A 

[21! 



W6FM(vi4) 



EWABLC 
FILTER B 




ISM Cfc»*i 
ENABLE 
SCAM 4 
SEUCT A 



-l&jli?>> 



ISM <»»^a 

APU 

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eN>^BLE 

usbamtcs 
/red; 



ISM a^t 

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CM 



R&V 

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COMP 

LOAD 
1 



ISM fii») 

ENABLE 

WBP>I 

tpei» 



COMP 
LOAD 

OKI 



J^ 



POWER t*i-n 



COMP 
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5 
OKI 



Jm 



ALL 

SHUUT 

LOADS 
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P0WERC 4fcO 

VERIFY 

TOCK. 

[^ 



VMBFM b>r») 



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WBVTR 1 
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IN&FM^I^ 
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DAT^ 
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FILTER A 

DISABLE. 

•PSM : 

RELAY ajS 



EC^AH 
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ORBIT 

ADJUST 

THRUSTER 

HEATCR 
OFF 



^ 



MAGNETIC 

a>lP£rJ5*Td? 

CNAGLE 

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SPARC 
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APU 

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OFF 



\>i5ABtt 
USB 
XMTCS 



COMMAND 

PESIGWATIOW 



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CAOI 
CAIO 



CJOCHAKJKJELB OFF 






CBOO 






Ten 



CIU COMMAND 



6*IITCH 5/C REGULATOR 



SWtTCH STADANmSFN COMMAND UNK^ ' 



_<;^MM ANDCLOCK_P VQO MOEC & O M_ 
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SWITCH S/C REGULATOR 



CIU CHAVJNEL>* OFF 



_ CIU CHANNEL A ON 
'lHMANDCLOCK._ES/c6Mbet5 ON 



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APPENDIX C 
TELEMETRY MATRIX 



I 



* « 

* 1000 - ATTITUDE CONTROL SUBSYSlfM * 
^ ^ ^ * 



J 



I 
to 



n?>47J222902AY RFV B PRTS ELprTp'rnAL SYSTRM?! SCHEMATlcyTELEMETRY MaTrIX ot/i9/74 



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TLM FUNCTION 



ACPONYM SIG^JL SamP GATE COlUHN VIP 
TYPE SEC ADDR /ROW CONN 






IKT 



PAGc 












FORWARD RCANNf^R STGNaI PROCESSOR 
lo o t ^D-S^UJif^^EAD E AR TH P ULSE 



100? '^^ SCAN TRAn EARTH PULsE 
100^ ^^^ SrAN PRES*?aRE ^ 
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FSn L FP A4AG jy-^6 AjpftA 15 q9 



100^ •^'Q srAM ref processor card temp 
too* *^wo SCAN lypsine down 
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FSC T EP 
FSC PRES 
FSr p A T 



ALOG 
ALOG 



FSC RP T ALoG 
FSC UPON ALOG 
F Sn TF K^P AtOG- 



l/l6 
l/l6 

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Al70 
A?33 




iB i8 4TH2. 
C P 3? 4 TH 6 1 



A526 55 69 
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4T92 



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6Tq(,.72 

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7ll2-fi ^ToO-74 
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^EAP SCANNED SIGNAL PROCESSOR 



1010 
1011 

-i-or^ 

1013 

ini4 

1 C 1 » 



^EAR SCAN LEAP EARTH PULSF 
^EAR SCAN TRAtL EaRTh PULSE 



RSC L Ep 
RSr T FP 
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ALOG 
ALOG 
A LO C 



^EAH SCAN PNEAiP CTARn TEhP RSC PA T ALOG 

^EAR f?CAN ftfF PROCES^nR CARD TEhP RSC RP T ALOG 
^ E A R ^c ^*^ ur s tQE nn ns ' n?SfT uppn — ^loG 



1016 ^EAR SCAM MOTP** TEmP 



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CI 37 4TH6 
C? 55 4T9o 



RSr TEhP ALOG 1/^6 A553 1? 73 4T94- 




6T01-42 
6T0I-43 

T-0t-*1)- 
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AToi*41 



1020 ^^LL 1 EAD AhP OUTPUT 

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102? 

102^ 
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102^ 

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^OLL REAR MOTnR DRIVER (cw) 
^OLL FWD FLYMHEEL SPFFO 
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1026 ^OLL PNEuMATIrS MODULATOR 
1029 ^OLL COARSE ER^OR 
-44^l^„^.-aOtJ^.^JMP EPRri3 ^ 



1031 ^OLL niFF TACh Ahp STATUS 

1032 ^OLL SOLEMOIO DUTY CyfLE 
Iflll ifAtf MOTOR nPTvFH fCHl 



1034 YAW MOTOR DPIVER fCCy) 
1U35 YAW TACH AMp oJTPUT 
1q36 YAU pmFU maTtpc Mnngt f TOP 



1037 YAH SOLENnlD njTY CYCI E 

103^ »itch motor driven <crH) 

1039 ^ITC.U MHTHfl npi^cp f^u^ 



10^0 
I04l 



'ITCH COARSE FRHOR 
>iTCH FINE ERROR 



RRmU CCW 

RFmD CCW 

-&FmD c^ 

RRmO Cw 

RFfh SFD 

RRFW SPD- 



ALOG 1/16 
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ALOG 1/^6 
AL06 1/1 



Ain^ 

Ai^B 



R PN MOD 
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ALOG 
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Ip O' ^T'io-i7 
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C6 00 

r7 00 



4T9fe-69 
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Cf 47 4Tt^8-oT^ 
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Ce 64 4T92-1V 
U 73 4T94-17 
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7001-50 
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■4i ^ ^Toc-t6- 
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^Ton-1^ 

^T.^fi*^5- 



Y mD CCW ALOG 1/16 Ai66 cB 1^ 4Tb2»54 7ont-ll 

Y TACH ALOG 1/1 A6f^7 ,:t qi 4T96-74 7nol-l? 

Y PN -4iCU) ALO G ^^ A.^i4 M-^^ ^4LTi!4-a4 ig^^-iJS- 

A296 IP 36 4Tfi6-i7 7Qnl-l6 
A362 c** 4^ 4Tbfl-fii 7o(5i-43 

JIA^4 tS^.5A 4T9Q-31 7ool-47 



^T{]n*22 
^ToO-37 

6T0O-75 
(tTfj(j^^5 



Y sol nc 

p mD CCW 

p md nn 



ALOG 
ALOG 

Ai nfi 



1/16 

l/t6 



P FH CPS 
P FR FKiE 



ALOG 
ALOG 



1/1 
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A6q8 

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07 01 
04 0? 



4T96-16 
4T96-o7 



7oOl"26 
7ool-34 



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6Too * ^2 



6Too-?3 



DP47J222902AV REV B FRTS eLpCTRirAL SYSTEHS SCmEMATIC/TElEMETRY MaTrIX f^t/i9/7A 



PAG£ 



FJNC 

N3» 



TLM FUNCTION' 



ACRONYM SIGNL SamP GATE COlUHN VIP 
TYPE SEC aDDR /ROW COMN 



S/S 

CC^^ 



IKT 

CONN 



S o 
^ W 



o t^ 









I 

03 



04? 



^ITCH TACM 

»ITCH FLYWHFEl SPEED 

^ UCH PJt^ mflTtC HnpUiftTng 



P TACH 
P FW SPD 



ALOG 
ALOG 



l/l6 
1/1 



A4fl6 
A6n 



CI 64 
05 02 



045 »ITCH SOLENOin DUTY CYCLE 
q46 3,A,/ACn MODE STATUS 



P PN K OO AUlfi t^i *^\^ — I g 00 



4T92'-54 
4196-83 
4T96-5g-^ 



04fl (n»5><l.ft ) (3.^ * 



049 ;H US>.Qfl-J* TN I fS PHC M P OSI T B1 



DF^l PTTCM POSIT 
BTAS J^TATIIS 

ASJL 



P SOL DC ALOG 1/^6 A^^q C? ^3 
OA/AO ST ALrtG 1/^6 Aq'^ 0? 0® 
YBrAs ST — HUG dUl^b — A^SS — c" 1^ 



41^4*54 
4T8(j-74 



700l-l7 6T00-1* 
7^n^27 'ftT00-p4 
7ooi^lD ^f^H5^"* — f >* 10 * 11 



7oOl*33 

7ooi-i« 

70Q1"3 



^Tnn-.^o 

AToo-79 



PBfAS ST ALOG l/i6 A23o lO 2^ 4T«4-54 7ool-2 AToo-^S 



fAW POSIT BlAq/ RMp A/IJ STATUS 
05n ^nCH AND HOLI HQm. iiMLOAn 

^^ ,rm VPLTftrF^PfEM TMTgPLnCK 

05? »NEU INTFRLOCk 0YPASS 
AND YAW F!NF CO^»TROl 



PYPHp ST ALOG i/i6 A2fi7 12 35 4Tb6"74 7ooi-2o 6Tt)0*i7 
PR UNLD ALOG 1/^6 A3Al G? 46 4T86-pi 7onl-37 ftToo*:^2 
I.V/P UIT AUiG t/i^ AA^fl H»-&^* 4T9o-fig 7o fl l" 46 «iToo «< l 



-f^ »3^^^Ua-R4 ^ A S p A. C l . OCk 



YFW C 
-CLOCJC 



EN 



ALOG 
.ALnG- 



1/16 



A485 
-Ak54B^ 



IP '63 



4T92-31 
_AT94-?S^ 



:Le PHASF B CI OCK CLnCK B ALHG 1/46 40^4 CI 
:LB PIUS nR MINUS 10 vOLT supply ♦/- ifjV ALOG l/i* Al^Q C2 

f^A ^X^a-RUiS^- nR MT- JiJ S A yJ i L T S U PP L Y 1/- 6^/ AL nG 



054 

n5^ 



057 :lb ppwer supply VOUtAGE 

05B :l9 MnTOR Dt^lVtR ^^Rn TFmP, 



ri6n ^INA INTO YAW OUT/IN 
061 ^00 ^PW InTFRIK ors/p^ 
^^^ — ^r iL L i \ ^or E nnio oN/f i FF 



063 ^OLL * SOLE^'OID flN/oFF 

064 ^TTCH ( ) SCLF>IOln On/OFF 

<l63 ?4IIUi- (^->™SaLF-ii)tn-QK^£^- 

g6^ rAW ( ) SHLfNOlU ON/OFF 
067 rAW (-) SOLFNOlU ON/OFF 



P/S VOLT ALOG 1/16 
HTP Dtt T ALOG 1/16 
PS C RD-T AUtG 

rlma-yaw dig b 1/16 

4on ^^^ D^G B 1/16 
R ■ SOL DIG R 1/1 



.^U^ A-^^3 1*- 



4T*^0-5o 
4Tfi2'5o 
41P4-31 



R - SOL 
P SOL 



DIG B 
DIG B 

DIG a 



SOL 
SOL 



DIG B 
DIG B 



1^1 
1/1 



A3A0 
A484 

pB48 
2B49 
ft Rl3 
5334 
5B35 



Cl 46 

15 63 

lO Ql 

12 01 



4TV2-5? 

4T02-34 
4T(j2*io 



7001"29 

^001-21 

7onl'23 

?ooi-^ 



7ooi'3n 
7oni-4 

7oni-36 
7oni-44 



6Too-?6 

^Tf)n-7n 



6Ton-77 

6TOO-T 

MOO*<»1 

6TOO-39 



i » pa — 4Tng^3i 7oni-i5 — ^ Tf)n- i 4 



17 o2 

It 0^ 



1/1 
1/1 



7B33 
3B37 



l7 o3 iJ^ft^ 



4To^-74 
4T04-28 
4Tn6 -74 



i6 02 
1^ 04 



4To2'-7o 
4Tofc-66 



7onl-4ft 

7oni-49 

7 0Ol' -3^ 



70Ol"3l 
7001-14 



6Tor-^3 
AToo-^4 

6TO0*P^ 
6ToO-l3 



YAW RATE GYHO (YRfi) 

_tfl7fl »a4-UQlJ SlN G-lc^ P E R A Tu fl 

107i fRG WHEEL SPEFO 
107? YRG ImDICATFD RATP 



U.JUS- 



YRn + QPf** 
YRG RATE 



-4:H^ A^&54 IP 0^ 4Tfto-a9 ^e^^ 3 f TQi - 13 



ATnG+ 1/16 AA57 C5 1' 4Tft2-2^ 73o2-5 
ALOG 1/1 A6i3 13 0.4 4T96-31 73o2*i 



6T01-14 
'^Toi-l? FH 10*1 



^ate measuring package no 1 

-j^^fl ?MP SU PP L Y V Qt-T A G F Nn 1 



RPl PS V AtCfi 1/^6 A2^ Dl 2ft 4Tft4^ 3 r i — Z5^-^m^ ^Tqi ■ ^q 



lOBt ^MP MOTOR VOLTAGE NO i 
1062 ^MP MOTOR CUHpENT nO ^ 
IQflJ ^MP A HEATER PQWFP 



R«1 *o V 
RPl mT I 
RHP HTRP 



A .♦+. 
ALOG 
AL"^ 



1084 ^Mp GVRO TEMpFRATliRE NO I 
10B5 ^Mp pACKAnE TFHP «0 1 
1 8 6 ^ Mp INDIC A TE D R A TE JH^D lUM 



RPl GY T 
RPt PK T 



1/1 
1/16 



A35i 
■ AfliS 



10 
35 44 
-4fi S3 



4T86-511 
4T68-74 
4T9q-74 



75q2-4 
75o2-5 
7 5 5 -7 



ftTo -Ai 
'*^Tol-^2 
ftTol*#4 — 



ALOG 1/16 A479 Q) 63 4T92-74 75o2»9 6Tol-^5 
ALOG 1/16 A543 C2 72 4T94-74 75d2-1o ATqI-^^ 



RESOLUTION) NO 1 



RP| IB M ALOG 1/1 A6i4 0^ 02 4T96-54 75o2-12 6Toi-fr8 



Di'47J22g9ogAY REV B FRTS ELgcTRtCAL SYSTEMS SCHEmaT Ic/TELEHETRr MaTrIX ot/19/74 



1 


N3« 


TIM FHhicTlOlv* 


ACRONYM 


SIGNL 
TYPE 


sahP 

SEC 


GATE 

aDOR 


CrLUMN 
/ROW 


VIP 
CONN 


S/S 
CCKK 


INT 

CCnn 


'C 3 
























' 








1087 
ttW- 


^Mp INDICATED RATF (HIGH 

RESOLUTION) NP i 

^WP gPI Av niJniiP ft_qT^TVS mO 1 


ftPj IR H 
^l ASTA 


ALOG 
ALOG — 
ALOG 




A6o9 


09 01 


4T96-03 


7502-11 


6Toi-ft> 








106^ 


^MP RFLAy GfiOtiP, B STATUS NO J 


RPl esTA 




Ax56 


t5 a^ 


4Te2-30 


75o2-2 


ftTQi^r,fl 






) 







D?%7^22290ZAY REV P F*^TS ELfCTR.1CAL SYSTEMS SChEmaT ic/TELEMETHr HaTrU ^t/i9/74 



PAGt 



FJNC 
NO* 



TLM FHmcTIO^^ 



ACPONVf 



SIGNL SahP gate CClUmN VIP S/S IM 
TYPE SEC aDDR /ROW COhN CCKK CCNf; 












10^0 ^WP SlipPLV VOI TAGF No 2 

lo^t ^hp motor voltage MQ p 

IQ^p jjiP-^H^TQR CIIRPEhlT MO ^ 

lO^i ^"P HFATER POWER wO ? 
10^^ '^'* ^S^^*^ TEMPFHATIJRE MO ;>, 
IpQfi ^WP p a CK A fiF T C iPFR A T il BE' M n a 



^HP IKOlCATEO RATF <MFDU|M 

RESOLUTION) NO ? 

WP ir . ' D TC A t f^ P A TE < H|c ; H* 



RFSOHITIONJ NO 2 
lO^ft ^'*'* RFLAy group a STATUS kQ 2 
-4-ftM aMP B t^ LA y GROUP fl S T A TUS NO 2 



INITATION TIMFR 






INITIATIOM T!>^ER J ^5 

INITIATION TIMER T*?o ' 
|M^T]ATTnM TTMPff DCSdT nMiOFF 



aNEUMATlC^ 



12in 3AS TANK TEMPFRATr*RE 
ipj^l HANirOLH TEmPFRATURE 



I2i:^ i^ANIFPLO PPE^SURF tLOW) 
iOLAR._ARaA4f-4)RlJi£-XR4i^Hl4^ 



RPp PS V 
Rf^9 MT V 
RP? NT 



*LOG 

AL06 

-AUlG. 



RP? HTffp 
RP? Gt T 
RPp PK T 



ALOG 

ALOG 
ALQfi 



1/16 
l/l6 



l/l6 
l/l6 



A2l9 le 25 



4Ttt4-fe9 
4T66-29 
4Tfift*5& 



A4i4 15 53 

A47B iP 62 

-ASA^ CI 72 



4T9o-5d 

^T92-5o 
4T9A*^f^ 



76c2*3 
760S-4 

a^^5- 



76o2*7 



AToi*54 

ATol*^3 

^Toi -A^ 

AToi-7fl 

6T01-75 



RP? IP H ALOG i/i A6i6 o^ lo2 4T96*i7 76o2*i2 nO^ ^^ 



RP^ tR H 
RP? ASTA 
RPp BSTA 



ALOG 
AL06 



l/l6 



A6i7 
AO^l 



07 02 
J? 0^ 



-M^ — a s 1*^ 



4T96-JJ1 
4T«o-69 
4Tf ip*ft9 






ATQl-Rl 
ftTol-*?! 



l5S TMR 
5ft*i THP 
JtMR RST 



ALOG 
ALOG 
DIG B 



l/l6 
l/l6 



A2lS 15 25 

A2ft4 02 35 

-4B*e 01 - 00 



4Te4-43 
4T*>6-3r* 



^Qn3-7 



^Tao-P4 



TA^'K T 
HAvFlD t 
tamk P 



alog 

ALOG 
ALnG 



MA^FlD P ALOG 



l/l6 
l/jfe 



A349 Jd 44 

A4i3 12 53 

-tj^J 15 6 2 



4Te.8*29 
4T9(,.29 



77,';2-3 
77o2-5 
77a £ ^9 



l/l6 A541 IR 71 4Tt4-?^ 



77 



6Tol--^3 
^Toi-<;5 
^ Toi -<; 7 



C5' 



ftToi-*>6 



1220 SAD RIGHT MTR. WINDING VOL T 



1222 
122^ 

122*^ 
122^ 



1229 



SAD RI 

3AD RI 

- SAD R4 

SAD RI 

3AD RI 

SAD RI 



SOP 
SPg 



Hwrv 

T A CH 



ALOG 



GHT HFCH HOnsUn TEMP SOP MHGT 

GHT MTR WINOING TGhP SDR HWPT 

GHJT— EJiO-SUl^-^ tws^ia-XHH S DP FSS 3 

GHT REAP SUM Su^S^R TEHP SDP PSf T 

GHT SUN SEN«?nR pREAhP OUTPUT *^DP SSPA 
GHT r^5lf nOfcivFoTFR SHft ^ if i V 



SAO RIGHT HOUSING, PrtF*?SURF SDR PRES 

3AD RIGHT RATF BUS NORwftt /HIGH . SDR RATE 

■^Ai)-4»LG HT PH A <;P Sw iT fUJ-^CM / C CW , S Dr P HKW^ 



ALHG 
ALOG 

&LOG 

ALnG 

ALHG 






alqG 

DIG B 

^niG-B- 



l/l6 

1/1* 

1/1* 
l/l6 



A6i9 



C9 00 

CS o 3 



l/l6 
1/1^ 



AO'O 10 0^ 
Al54 1? i6 

t-a i7 1 ^"^^ 

A2**3 C3 35 

A34S c** ^^ 

-^^^ lO ^ 3 



4TVe-3^ 
4 T ^ ^ - 1 S 



A476 1? 62 

2^5o 15 01 

-2^^! — l*-e4r- 



47*^0-^3 
4TC2-43 

4T£i4:=L 
41^6-6^ 
4Tfife-30 
<T9q-3f^ 



4T92-30 

4704^^3^ 
4To 4 "in 







a 

I 

o 



Di»47J222902AY Rpv B FRTS ELpnTRIcAL S-TSTEMS SCM^MATIc/TELEHHTRY MaTrJx o^/l^/^-l 



FUNC 



TLM FUNCTION 



ACRONYM 



SIGNL SamP gate CCLUMN VIP 
TYPE Sec ADDR /row CONh 



cc^^ 



IM 

CCnkj 



PAGt 



SOLAR ARRAY URlVE <LEFT» 



l?4o SAO LEFT HTR wINDTnG vOLT 
1241 SA'D LEFT TACM OUTPUT 

l?*1 p ; AD LFFT M ETh HO j iriNn TC m P 

1?43 3AD LFFT mTH wINDTnO TEMr 
1244 SAD LFFT FWD 5;UN SEty<?nR TFMP 

4^f^1^-R£A.ft.-SyS™Tl£jwP 

1246 SAD LFFT SU^J PENSftft ppE^mP OUTPUT 

1247 3*0 LFFT -^^V CQNVERtfR 
iP 4 fl s a p LFFT u n i ?Sr4G PRF fi SUftr 



124*» 
125n 



SAD 

SAD 



LFFT 
LFFT 



RATE BIAS NrtRMAL/HI 
PHASF SMTTCh CW/CCW 



SOL Mwnv ALOG 

SDi TACH ALoG 

-SJH — HH^ ALnfi 



SDt. ¥U[>T ALOG 

SDt FS5T ALOG 

-SP l B S ^ ALO£ 

SOl SSPA ALOG 

SDL -iSV ALOG 

S Dl . pfi&S flLQfi 



SDL RATE 
SDL PHSW 



*JOTF 



DIG 9 
DIG a 



1^1 A631 c^ tj3 4T96-53 

Ul A632 o7 o3 4T96*33 

-t^t^ A^^^O H.^^^^ A T9il-3„ 

1/46 - - 
1/16 

A ' 1 
i/16 



Ao*9 CP 0^ 4TaQ-24 

Al53 10 1* ^Til2-24 

V S ^ i p g5 4 t£A-^^ 

A2e2 18 34 4Tb6-43 

A347 c? 44 4Hi6''69 

A *1il L '' 53 4 T<^pr6'f 



7422-11 ATol-20 
7423-16 6Tol-?4 
7^g3*g ^ T q i i ^ a 



7423-in 6Tot-l' 
74?3-22 ^Tai-:io 

74?3-l6 6Toi-?6 

74?3-2o ATni-?« 
7 ^g g'l 4 ^ Tfl^ ^y g 



1/16 2B52 CI 02 4Tfl6-34 74:33-17 fyjU^p^ 
1/16 2S53 02 02 ^To6-H| 7423-12 6T0I-PI 



ALSO SEE FLtCTRiCAL IMTERFACE S/S 



4CS STRUnTUPAl TEmPERaTMRfS 



-±26^ ^S^PMTF 1 TC HP ^u^ 



\?.fi^ SASfcPlATF p TPMP y 

l?6p SASEPI.ATF 3 TFHP Y 

-1 36^ TH E RMH Stillf L n 4 TFfip 



l?64 THERMAL S^IFLP 
-4,^66 JJ-JERi 



1267 THEf^MAL SHlttn 
l?6fl LOUVEp HpifSJNP 
Ig ft ^ — gmv^a^jimiSMtr HinpntMT ^^ TFMP 



5 TEMP 

6 TF=Mo 

<i TEMP 2 

XFND g TEMP 



-X 
-Y 



l27o 'WD IP SC^N^6P MTG-i-, T^p' 
127t .^FAR tR SCAfrjNFR MTG 1? TFhP 
I37n PMEU^^JU A.T^-HTfl iMtHfli 



1273 ,nwER SrpuCTUPE AT t*AcE 

DF Cylinder i^ te^p 

-4^2J PNEM fYt TOP ^q TFmP 

1275 LtFT ^AO pADIaTOR ^6 lEHp 

1276 ^IGHT SAO RADtATOR 17 TEhP 
12 77 UUiUZ^MEu VOLTAGE 



1278 YAU NOZZlP arm 2q TEmP 

1279 ^tCHT+X RADIATOR j8 jrMP 
tPfli) nilVCP Mrill<;TM/^ -V FNn ^0 tcmp 



-^«fli^-Y AtoG^ 

THn2PP X ALOG 
THn3PP Y ALHG 
TH n 4TS Y AUifi^ 



THfit>TS-X ALnG 
THo6t3-Y ALHG 
TH i^ 7TS X AL^Ci^ 



-1/^^ A475- 

1/^6 A539 
1/16 AoOB 
1/^61 A l^g 



1/16 

1/16 



A2l5 
A2^1 



12 7i 
C2 0^ 



THptlTS Z ALOG 
THf^iLH X ALOG 
THpgLH" lUlXL 



THpiFSC ALOG 

THft2PSC ALOG 
vlUX^f AW)£^ 



1/16 A4i^o 
l/jft A474 
l/jft A*5 3 e 



1/16 Aofl7 
1/16 Ai5i 



cP 35 

:*^ 34 

C? 53 

CP 62 

U ^1 



-J 1^-2 = 
4794- 

^Tflo- 
4Thpi 



6^ 



4T>^< 
^Tfi6- 

4T92- 

4TV^- 



69 
11 

24 
4^ 



43 
43 



^lf)2^ 

«ln2' 
^lfl2- 



-fTi^t*7^ 



CI 0^ 

h:?--25- 



4TH(j- 
4Tft?- 



46 
46 



**102 
Pl02 



2fl 6TQ1.75 
29 6T0I-74 

M — A Tfta - 73 



^'lOir- 



'12 6TQ1.72 
'11 '^T:ii-7-L 

HJ ^^fl^7^- 

'3o 6Toi*77 
'1** 6Toi-in 



1^ 6T01-27 
l4 6Tol-:^5 



THnlLSCB ALOG 1/16 A2'*o 12 34 tiet-n eic£-l3 6Tni-38 

THnlUHY — AU n G 1/^6* A3fl5 ^i-« 4Tefl-p< Rin;:"3p Mift^^xSlL 

THfiiLRAO ^LOG ' ' —^- - - ' - ^^ ^ 

TH^lRRAD 

TCh n 



1/16 A267 
ALOG 1/^6 A473 
*L0^ 1^ 1* A 537 
THnlYN7L ALOG Ul^ A344 
THnlPR X ALOG 1/^6 A449 
THn3LH-X ALOG ^J^ A4'i6 



15 32 ^Ttf-7? ^102-33 6T(ji->i5 
C? 62 4T92-2^ »102~3^ 6Toi-4^ 

^-6^24 AT^4*2 J 8^1re-2 =^ fr — AT-o i-ii4~ 

15 43 4Tee*ii ^102-37 6Toi-P3 
15 56 4T92*23 f^ln?-35 6Ttjl-49 

-45-aS 4T9g*i : ^ filQg-^6 6Toi,qo 







> 


■ 










*-fcA 


NUMBFR 2000 ' 


*JtJtAA* ******** *L*AAA^ A_*JlA*^ 


lA** 










-' 






• 0R8IT ADJUST SUBSYSTEM 














\ 


♦ •♦ 




»«*******««**At#**«A^«***4 


Jktt« 






-. ^. 








. 




« 










.— .. _ 
























. 




r\ 




















^ J 

1 
-J 





















DP47J22290ZAY REV B FRTS ELfCTPICAL SYSTEMR SChEHATIC/TELEhETRY MaTrIX ^t/i9/7A 



PAGt 



O 

OD 



FUNC 
N3. 



TLH FUNCTION 



ACfiONYH SinNL SamP GATE COlUHN VIP S/S IM 

TYPE Sec ador xpow conn cckk ccnw 



OnoiT A QJUST n/ B 



-^tnrl ^" OP E lLA N T TA ^' K Tr M PrRATunE 

200^ THRUST CHftHREP NO. 1 TEMppRATUPE 
200^ THRUST CMftMBEp NO. 2 TFMP^flATURE 



P T A N K T A LD C 



/t* A^^^ fB—^ 4 T8 o *i3 «^-{f 2 - »€- 



^f^ — r MRu eT_CH * wH6n n o , 3 rr M Prn A T URE 

200^ 



CHhS I T 

CHhB 2 T 



ALnG 
AinG 



CH hB 3 T A LO G 



/l6 
/16 



A341 

A4o5 



OP 43 
10 52 



4 T 88-5 
4TV0-5 



Aj^^ AAS^ ly * 1 4 T9 9 » § i 



^on3-T 
5on3-7 



*im^ 



.'INE PREs*iUPE 

SOLENOID VALVP NO,i ON/OFF 



tlwE P 
SOL NO 1 



ALOG 
DIG e 



S QL N O g DIG 9 



^f^^ — soLEwnio vAi v^^^J^Org^-fwy-nF-g- 

200^ SOLENOID VALVF NO, 3 OM/OpF - SOlND 3 
»niE RpP PlcnroirAL TuyF^^^^P ^^^ 



/16 



A534 le 7o 4T^4-i 
7334 17 o2 ^To4-7 
U 



DIG B 



3 &003-R 
7 5oo3-A 

^ . ^ ^im3^- 

7S37 16 0^ 4To6-7o 5oo3*E 



-^Ta^* J^7--fr3 4 ^ 6-7 



-It 



* :^000 - ATTITUDE MEASUREMENT 
-^ S E NSn W S UBSYSTE M 



CO 



D»47J2Z29o2AY RFV B FRTS ELfCTRTCAL SYSTEM?! SCHEMATIC/TELEMETRY MaTrIX ^t/x9/7A 



PAGE 



9 


FUNC 
ND* 


TLM FUNCTION 


ACROWYN 


SIRNL 
TYPE 


samP gate 

SEC ADDR 


colUmn 

/Row 


VIP 

CONN 


S/S 


IM 

ccnn 








iTTTTIinC uCACiiaCMruT rciif^ftP ^ 


















' ■ f 




3oor> 
3001 


1-ROlL SIGNAL 
-ROLL SUNAL 


ROLL -r 

ROLL - 

pItCh ♦ 


AL06 
ALnG 


1/1 A624 


0^ 03 


4TV6-1H 

4196-0^ 

Jl T Q JL V ^K 


5Gf,3*A 

bGc3-B 

C ^ _ £ 








300* 
8nrt^ 


•PITCH SIGNAL 
FEMPEPATURE NO,i (CA^F) 


PITCH * 
CA9E Tl 
ASSY Tgi- 


ALOG 
ALOG 

"^M.OG — 


I'l Ao-?*- 

l/l A626 
i/l6 A4oe 
1/^6 A47g- 


04 04 
16 52 


4T96-Q6 

4T9o-ii 

4 T tJ I** * « 


— ^Cti?** 

56f,i-F 










^iOTt SEE ELECTHICAL- INTERFACE S/S 


— Qi"62~ 


^ ^ ^g 11: — 


































\ 






















^# 






















*S^- ., 


















*x^ ^ ' ■ " ■ ■ ■ __ — . 











* MA^GNFTlC HnMENTS COMPENSATING AESY. 
"* — HiH^ 



o 



9 ^wc 

M NO* 
to 



nP47J??29o2AY REV fi FHTS ELpCTRICAL SYSTSMS SCMEMATlc/TELEMETRy HaTrU ot/l9/74 
TLH rUNCTlOM 



PaG£ 



ACRONYM 



sigNl sahp gate CClUHN V]P 

TYPE SEC aDDR /row COhN 



sys 

COKN 



I^T 



<001 30ARD Ai TEMP 
400?* 30ARD A^ jEMp 
-H\r^ 4Att"-&E-NSAJ*--Ct^Rt>+^ 



♦oo^ TAW Flux newstTY 

4oo5 'ITCH FLljy DENSITY 

4 Q^ ^nUL riUx DFNrlTY 

4ot)7 »OWFR OM/OFF 
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1/16 A375 
1/16 A4,^9 
^V-j^i A^/^7 



Alt8 

Aia? 

A3l0 
A374 
A4nfi 



15 20 4T<^2*56 
1ft 26 4TH4'74 

Cp 48 <tT?^e-5ft 
CP 57 4T9q*5^ 
I f 75 4T^4-ft^ 



^Ti?-23 
5T2Q-23 

5T12-21 
5Tn^-?? 



7N\/0iTM 
7NV02TH 



ALOG 
ALOG 



ZNVUpSM 

THpSmm 
THTASM 
THPHyP 



ALOG 

ALOG 

-J^4_nG 



1/1^ 
1/16 



1/16 



A5ol 
A566 



7fl93 ^RV CAMERA fiUPPORT BpAMtCFNTER) THpBvPC ALOG 
7o94 rfRVTR RAniATOP (RnpT* THwBrrr ALOG 



ALOG 1/^6 
ALOG i/^6 
ALJiG i /-t^- 
ALOG 1/16 
ALOG 1/16 
AtnG jy^ 



Ai8i 
A2?l 
A 3r]0 



U 11 ^Ten-55 ^To4-4 

12 2(j 4T62-5^ tTi2-< 

-4:U:4-£i.i ^?i3-4^ 

1$ 33 4TH6-5^ $To'''3 

di 48 4T88-5t» ^Ti2-3 

C g> ?7 tf T9Q>^^ 5>T]rD - g 

02 66 4192*3^' 5To4-2 

ip 75 4794-5b *.Ti5-2 



1 ^ 3^ 



4TH2'3^ 

4764-2^ 
4 T ^ 6-3^ 



A373 ifl 47 .4T^6'3? 
A437 ci 57 4TS'g-32 

A^ij— tt-^^ — d::L&2^7^ 

A443 18 57 4T^o»7^ 
A444 01 56 4T/JJ-79 
-AA45 CF "^ft ^y^Q-Sfc 



^To4-2o 

^M?-2n 



^O^*^ -JQVTR Hf^AT STPAP iHyBRNS ALOG 

7n97 <jB tLPCTRnUICQ HOHnT nVFR BAY NO. 1 THqIWRE ALnG 

if^a£ il R FLFnTa mx TH'; MPt I NT nVPp R AY NQpfl tH ^^L^Rp A|_n G_ 

7(199 ^flVTR 1, TNHOuRO nF 5?FPARAT0R 3 THf,3wBP ALOG 

^lOn ^0VTR t- INF*0*^D nF SFPAraTOR ±7 TH,7uBR ALOG 

2^(V4 dBM iR^ i , rFh.TF j3 THriuPP AL^n 



1/16 A446 ie< 58 4T9q*35 

1/16 A447 ip 58 4T9Q-57 

-1 /^ ft ASgit — H > 66 _4I:92.*^5„ 

l/l^ A5o5 16 66 4T92-(j;? 

1/16 A5n^ 1^ ^* 4T92-19 

-4^.^,6 tSflJ CI '^^ — ^TVg*<^r 



^Tn4-6 
5T12-6 

^Ti2-lf^ 
^T3£-34 
^Tgo « 3rt 

5T2n-3? 
^To^-3? 



7lo2 JPVTR 2* INf^OA^O OF RAY 4 
^lr)3 rff^VTR 2 PF^AM imBOArO nF RAY i5 
-U4^ ^9VTft ^t qpAri CPNTF" 



THn4gBP 
THrzwRR 



710*5 MBTR PEAh UB^ARO OF SEPARATOR N0*6 THf>6NBP 
7l06 ^RTR PEAm HBnARO OF SEPARATOR NO. i4* TH^ 4k'RP 



ALOG 
ALOG 

Al nfi 



1/16 A^tje G? 67 4T<^2*79 
l/l6 'A5n9 0^ *>7 4T92-5h 
-1^ 1 6 A gio 1 ^-fc 7 ^T?g-3b- 



^Ti2-io 

5T20-10 



1/^6 a5ix 
1/16 A568 
1/16 A^69 



IP 67 4T92-57 
15 75 41^4-0^ 
4£— Z5 A T^4*o 2 



5Ta'l-3o 
^Ti2-3o 



7io7 aRlP, pfA m C^^mtFr 



^_^ THC^igBP, 

71^6 iSS MOUNT NFAP SEPARATOR MO. i4 TH^4hSS 
7iq9 ^EAR rulkmeao QAS -Y THRupTER th-yoas 

M4^ ^SS MOUNT K 'FA o CFVTFq fl F uBtfTfl RFAM THrLlMQ^ 

7jll ^EAR BULKMEAO QAS X THRUSTER TH XOAS 



ALOG 1/^6 a57o (jJ 76 4T94-iQ 

ALnG 1/^6 A57i t)2 76 4T^4-7p 

-AUlfi aV.i 6 Ails c*^ 76 A\9 a^7^ 

ALOG i/jA A573 1q 76 4T94-5B 

ALOG 1/16 A574 12 76 4T94-35 

-AUUS tMA A57g 11^ 7 6 4T9^-*;7 



^Tis-2e 



5To4-l5 

Ml?-i5 

-^^^;--l^ 

bT(j4-i3 
5^2-13 
^gO'l3 



ALOG 1/16 A5g3 ig 66 4T92*56 5To4-io 



MOT£ SF E ELFCTRTCAl IWTFRFACE S/S 















* 




, S> 








-■ — — - 


— 




— Z^ ' — 















































-^ 


" 










L»-* ****^*****'+^**##'********A*** 













*^»< 




■ . — 


numpErs 8f,oo' ^oon* lonoo* ♦ i^poo * 












***« 


* 




— 


^ ■ — .. 






- 



















. 






• 


















— 


CI 














1 

bo 

CO 








1 







n''47J2229o2AY H»:\y B fHTS ELpcTRlCAL StSTEMR SCHtMATlC/TELfcMETRY MaTrIX o6/i9/74 





FJNC 


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N3. 


rf^ 





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TYPE SEC ADDR /POW CONN 



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ccnk 



14 



:OMMAWD CLOCK NO.BOOn 






3 



o 

td 






PRIMARY 
^RIMAPY 



chamnel 

CHANNEL 



jAJW*£t 



INpuT (DATA) 
INPUT f^TROBE) 
iPUT (HATAi 



PRf W IN 
PR! X IN 

B 




»0p,^ I ^F PUH n A h 

Snn^ REDUNDANT X CmANNFL T^>PUT (STROBE) REn X IN 

9oo5 SRIMAPY POvJFR SUPPLY TEmpfrATURE Pf'S TEMP 

" 0^6 ^£4)UNnAN^^CUjrj^^iiaP^- Y H^t/P .£ EATU R£ &^«; 

9oa^ *RI^^AP,Y OSCILIATOP Tfi^PERATURE POgC ThP 

BoQft ^EOUNHANT OSCTLLATOR TEmpfRATURE ROftC THP 

' PRIMARY nqrUlATQB HuTPHT PO<^r O I 'T 



-fr 



3oin 
Sqii 



^EDiiwnANT OSCTLLATOR nUTpuT 
ino KHZ MASTER CLOCK 



9013 2*5 KHZ 

&ni4 4f>n H7 PM A/PM B 



53 Sni^ ^EDUNHANT 4VPC 
5oi7 PRIMARY *S . o V*^*^ 






9029 



3o3? 



9037 

So3P 




3RIMAPY -^.pVT^C 
^EOUN^ANT -6,f,^DC 
PRTHAPY .rrl tfon — 



9f)2? ^EDUNHANT -?3^'0C 
9o2^ 3RIMAPY -^WDr 

90?*i »R1MAPY POWER SUPPLY ON/OFF 
90?6 ^FDUN^ANT .PGWpR Si'PPf Y ON/OFF 
9og7 aaijpp SUPPLY ^iFt FrX pflT./RFH 



PRIMARY COMSTO^^ OM/OpF 
9FDUNDANT COM<;rOR ON/fFF 

^ATP^XX^JIECXJDFP PRTMARYL/a^nilNEANT 
HATRIY IJRIVFR A PR I HaF Y/Rf DHNDAK'T 

•tATPiy nplVFR S primapy/rfDundant 

rRPOiiFMrY rtFW. PRTMAPv/RCnUNPANT 



«034 3FLECT 0?^ClLLftTOR pRi mARv/REDUNOANT 
9a35 5ERIAI OATA TRANSFER yES/AjO 
ft p^jik ^FfflAi Data Pp-^na vEc/un 



j^ HZ rA> yES/mO 
I H7. (B! yES/mO 
-?RlhARY Y CTHiM. Tf^PUTfFNAPlE) YES/NO 



9o4it 9^DUN. Y CHAN. iNPUTfFNAmE) YES/NO 
5o4i :oHHAND execute COUNtFR R!T 1 



REn Y \U 
CMP Ex X 



n='47J2gg90gAY ^^\f B FRTS ElprTfflC Al SYSTEH<? SCMEMAT Ic/TFLEMETRY HaTrU ot/i9/74 



FJNC 
NO* 



ACRONYM 



SIGNL SamP gate CPlUHN VIP 
TYPE SEC ADOR /row CCJnN 



S/S 

cc^^ 



INT 



PAGfc 



15 






■^ U O 



So4? :OMMAN*D FvECUtE COUNtFR RlT 2 
9n43 :OMMAND FvECUtE CnijNTFR RTT 4 
^0 44 ^HJlA-hLD,.^Hx£i:iix£^^nMNTF ft r|T R 



3045 :nHt^AMO FxECUTt^ CnuNTFfi HTT ^6 
9o4^ :nMMAK'D FvECUtG COIJNtFR .RTT 32 
^0 4 7 JffTMADY rn^STn'? ftli yF ^^/jti 




So4ft ^EDUNPANT COH^^TOR Fill YF?^/NO 
9o49 5RIMAPY COHSTnR AHTlVATF vES/NO 

9o5l PRIMARY nOMSTo^ VFRlpY YEP/NO 
8o5? ^FOUNPANT COm^TOR VEr T FY " vES/NO 
%*,? PfltMAP Y rnMnPn fM-sVi^r ^F * ;/"" 



^JOTE SEE ELEr. iNjERfACE 'S/S 



CKn Fx 2 DIG 
CMH EX 4 DIG 
CMP Fy a OJG 



^054 ^EOUNPANT CnMPEC TN-RYNC YES/MO ftCO SY^fC 
fl055 afllMAPY CnMDEr UATA FPROft YES/KO PCD ERP 

Z^^ — ^£iUi wJUAti^C aNm£c_aA.t A^ ppr^r YPfr/NH RCn tnn 



CMP fx3p niG 

pf nn^^ThF axu 

RCnnsTPF OTG 
pcdhstpa Din 

PCnMSTl^V DIG 
PCnMSTPV DIG 



8 1/1 

9 1/1 

9 1/1 

R 1/1 

f^ 1^1 



DIG 
DIG 



9 1/1 

R 1/1 

B t/i 

e 1/1 

^ t/i 

B 1/1 

5/1 
3 — 5/1 



2^33 

3B33 
-4i33i_ 
5B33 

6i333 



1S37 

1P35 
pB34 



16 02 

17 03 






?e35 

0932 



Ifc 03 
17 o2 
17 o 3 



1^ 03 
14 00 



4T j2*c>' 
4To£-6t 



4Tn?-47 

4Totf-fnj 



4To6-4l 

4T06-3V 

4T04-41 
4To4-ep 
4To6-fti, 



4To4-o;^ 
41^2-64 



i^Cii-rs? 

f^cn-14 

P'Cii-29 
^<^ll-3l 



5710-42 
5710-43 



2C11-2? 

2Cn-io 
^cn-2P 

PCll-li 

-^1 1 ' D 1 
2C11-03 
?Cii*2o 

-?Cji^--37^ 



•5710-45 
•5710-46 



5710-48 

5710-49 
-,57l-f>-^c<j_ 

57lo-*^l 

'?7in-^2 



57io-f^4 
57io-*55 



to 



.^M tU WJH^htXt GaAlnH-LUMX. 



9l0l -12V MONTTOP t^ 
-3^p ■igV PHMTTOP B 



3l03 -5V MONITOR A 
9l04 -5V MnNlTOfi B 

:-3}^^^rFMP-FRATtJR£-A 

9l06 rFMPERATiiPE B 
Bl07 :mANNFL a ON/OFF 

-Sl^flfi ?MA^MC| Q nNfOFF 

9io9 :nMMA^'D INPUT A CLK/CIU 
9ll0 :OHHAMD INPUT B CLK/Clll 

-i^-H ^S^N^FNAHI F A VPc/^n 



5ii2 iSFN FNABLE B YES/Nq 



»?Q1 



rEHPEPATiiRE 
._r£jiPFfiAIun£- 



B20-'^ TEmFraTUpE 
92o^ T^HERATUpc 



RF/IF A 
-J?Fv4t^^ 

demod a 
uemod n 



fl2o^ 

320^ 



620? 



AGC RFCEjvEfl p 

AUDIO AHPLlFIFfl A OUfPUT 

l i m in A rt ajjrTFff ft onTD iiT 

•SK DFMOnr»LATpR A OUTPUT 



ChjA-i^V 

riiiR^ipv 



cinA-5v 
ciiie-5v 

CI t l A T— 
ClM B T 
CHANNL A 

c:h6nwi ft 



ALOG 
Al O G 



ALOG 
ALOG 

ALOG 

niG e 
niG fl 



t/16 
1/1^ 



CMD IN A DIG e 
CHO IN B DIG B 

MSF ft FN nirt B 



i/16 
1/16 

1/1* 
1/16 



A244 10 29 
■^^^ 1? ^^ 



5/1 
1^1 



A562 le 74 
A467 x^ 61 

3^>s — e^^-^a- 

A5fl8 17 7d 
1^40 cP 00 



4T04'77 
4T90-47 ., 



?932 14 00 
3B35 If o3 



MSF B EN DIG B i/^ ^937 if o4 



'RF A T 
RF fl T^ 



DMnD A T 
DMnO B T 



ALOG 
ALfl-G- 



ALOG 
ALOG 
ALOfi 



1/16 
1 /l ft 



RCvB AGC 
AHPA OUT 

AMPft O UT 



ALOG 
ALOG 



1/16 
1/16 



A330 
A llg 



FSKA OUT ALOG 



1/1 A599 
1^1^ A243 

1/16 A36e 



A56i 15 74 
Ai76 15 1^ 
J^aB c < OQ 



;c5 00 



4T94-o^ 
4793-47 

4T96-7h 
4T02-3/ 

4U > g-g^ 



4Tn2-Bi' 
4Tn4-6^ 

4To6'02 



?f:4e-o'^ 

^C5c-oft 



2C5o-o7 

J'C4e*oi 



f'C4e-o? 

?C5o-o? 
?C5q-o3 



4T^8-45 

4T94-o*^ 
4Tft2-o^ 

4T<f6-i3 



4T96-4^ 
4T84-eo 



2Cot-35 
-^^^3X- 

?Co6-o2 
?Co^*o5 



OP 47 4Tb8 



2Co6-o9 
2^0^-11 

pCo6-i5 






o o 



n»47J2229o2AY HEV H ri^TS ELPCTRICAL SYSTEMS SCHEMATIC/TELEMETRY MaTrIk oe/i9/7^ 



FJNc 
U3* 



TLM FUigcTrOM 



9210 'SK DEMOnilLAToR B OUTPUT 
fl?|1 4*1 DEMODtriAloo A nijTptiT 

-ftg^^,„-4M_0t;Kani4f A.X()c^a^_ny two 

B?l.^ SUBCARHtEr? L£\/eL nET A OUTPUT 
S?i4 SHBCAPRIFR LEvEL PET p OUTPUT 
Qgj^^ ■l6,7V IJPMQP pQUeo * 



B?i6 

-J? 
9?l9 



6 



• ]*5*7V OFMOn POWEO 
•in RFG VOLTS A 

^EC/n»=HnD PnWF9 i/B 

^EC/riPHon pnwFfi «/a 




= CAM 

rCAM ON/OFF 



SCAN INHIPIT vES/MO 

= CAM FxEruTE/l OAD 

■J-CAH PUM..j^a 

rCAM PROnwAM/rOMHAND 

tCAM MEMORY TPMPERATuPE 
^MH^P0Wf^R-SUPJ=4^Y -TtHlS- 

ECAM VERIFY PLOW 

=rAM VERIFY ^LOW 

?rAM vFffiry fast 



l70l3 =CAh VERIFY FAST 



ACRONYM 



SinNL SamP GATE tOtUMN VIP 
TYPE Sec ADDR /POW CUfjN 



s/s 

cc^^ 



FSkB OUT 
AH A OUT 
-J^ H a OUT 



dhta out 

D£t8 out 

nMriA-^5v 



alog 
^L^G 



ALnG 

ALnG 



1/^6 
l/l6 



A496 
A432 

A6fj2 
A ^33 



11 0* 

1^ 7n 



UHne-i^V ALOG 1/^6 A596 i5 7^ 4T96*7i 
REnA-ipV ALOG 1/^6 Aq^I i5 o4 4Tii(j*2E^ 

-ft£a&-.^,V AtiiG t^.jA Ui:^^ J3^3 4i£-2^7a 

R/n SLOT Din B l/i6 4*343 l5 OO 4Tn4-4? 
SLCT R/D DIG B 1/^6 89^2 05 (}2 ^^O^^So 



^T^O-0^ ?Coft-l9 

4T96-24 2Co6-23 
4T96'43 ?Co6'25 



?>Cot-29 
?Cot-3i 

?Co6-b4 
S'Cofr-0** 



ECaM 
_^„CaJl„G 
FCaM Ik'H 
ECArt F>C 
FTftM BliN 



f^CAM PGM 

ME^'ORY T 

^HP S H T 



le. 01 4Ta4-3H 

1* 00 4Tu4-7-t 
16 o2 ^To2'-l* 
1 » 0^ 4 Tt)4i-7fi 



FCiih vfy 
fCftM VFY 



DIG B 1/16 oB51 
/1 6 6 D<^ 1 
Dir^ B 5/3L 5632 
DIG 8 1/4 9B33 

DIG P ^^ 7 B >^5 

nin B i/j 3B34 37 0? 4To4-9 

ANAL 1/^6 Al5o CI 1<» 4Tft2-i3 

-^HM. x^^ Mt^^ i^-^^ 4THAJ.ZiL„ 

DIG A 1/1 DAq4 35 o4 4TJq*29 

Oin A 1/1 nA<j4 33 0^ 4130-29 

f^ l G A Si^tj &A^4 13 00 ^^TlQ-^pQ 



1C05-2 

lCo5-6 

3Co5-4 



PAGE 



16 



IKT 

ccnn 



lCo5-3 
lCn5-8 

^c-tr5-7- 

lCll-7 

iCn-7 

» cii'y 



ECAH VFY DIG A 5/i dAo4 13 oo 4T3o-2^ lCll-7 



^** io*;i 

Fm 1[)#.ii 



n»47J2229o?AY R|=V K PRTS FLprTRlCAt SYSTFM*; SCHtHAT IC/TELEMETRY MaTrIK ^t/^9/7A 



?AGt 



l7 



PJhC 
NO. 



TLM rUNcTlOM 



ACRONYH SlRNL SAmP GATE COLUMN VIP S/i IM 

TYPE SEC AOOR ^POW CONN CC^^ CCNf^ 



fELEHFTHY Pf^OrESSOR *TMP) 






HFMORY SEnUENrOR DC/HC CONVERTER 
A VOLTAGE 

■^HE-MfMiY SEnilFfUrFR OC/nr fTDfc'VERTPR 



MSFQ A V ALOG I/16 Am Jp 10 ^TBq-iH F4T5t*? 









3 VULTAT.F 

MEMORY SEnlJFNr^R mqDiji E tFMPERATU«E 
rnp MATTPD nr/nn pnMVcpTFg a vni taaf 
•"ormatter DC/nc convfpter b voltage 

DIG MUX nr/DC CONVEHTER A VOLTAGE 

MG WHY nr/nn noNugRTPR g uni tagf 



MSFQ B V ALOG 

ME*vSEO t alog 

-TJiTfl A y. ALna, 

PHTH V ALOG 
DMUX A V ALHG 
OMMX R V ALOG 



/16 A558 

/16 A242 

4,^^ 6 A.tl5_ 







A494 
A241 



oe 74 419^-33 

D? j9 4T^4-o*^ 

P 65 4T92'33 
1 29 4TH4-,j6 
^-^^ 4TVo-3 3 



P4T5t-3 

P4T^ft*f> 

Ji 4 -1 2 0^1— 

P4TS0-* 
P4TJC-7 

P 4 TrM«ifl 



fgt^^l' 






'on 



fORHATTEr/OIGttal MUv HnnnLE TEMP 

ftMALflG Miiv DC/HC rnNvFRTER A VOLTAGE 
JLJIALQG -rtjj^IlC/,UC-raNvF,BXg 



p 38 4Tft4'(j9 P4T20'37 

ft 37 4TM6-1*? P4TV^.4 



4^ -4 b A J tfi - J3 EAX7Jt-^^„ 



k/d CONVE»TFR DC/nc 
rONVERTER A VnLTAGE 



COMV A V AtoG 



/16 A367 



1 47 4T''6^i^ P4T7^-i4 



7fl/3 



^014 



COMV B V ALOG 

r PMP A l 

PRFG A V ALnG 

PRFG B V ALOG 

RPPRCJG T ALOfi 



rONVERTER fe VOLTAGE ^, 

JiiHAi OR MUY A/n CIUiVEflTEfi-JflinULE- 
:>REREnULATOP t VOI T^CF 
^RERPGULATOR P VQ! T^GF 

?0i^-6 ^FPRQGRAmmER MfllliJLfi TFMP 

?0l7 MEMORY A nC/Or CONVERTER VOLTAGE HEM A v* ALOG 

Jfllfl HEMORY a MODUl E TF.mPFRATURE HEm a T ALOG 

^(^^ ^EMORY-^- nC/Jg^CQAiVER-TER VQtTAGE M£M_fl--V At-OG-^ 

^02n *HM(JRY B mOPU* E TFMPeRAThrE HEm B T ^ ALOG 

*n?1 ^OWER 1 OFF/Om POwER 1 , DIG B 

J^p-a ?nyFR 2 QFF/Oh' , POuFR-g aiG fl 



/16 A3o2 



5 37 4ja6^3.S F4T7<-j5 



Sl..ClZ_ 



/16 A4U 
/l^ A239 
i^.6 A44S 



2 56 

S 2^* 

P s a 



JLL9A - JLL_ 
4T9Q-iH 
4T^^4*lH 



_P_4-I2A=6_ 



F4T40-3 
P4T4ffl 



O O 



hrf o 









■^ 



/16 A495 
/l^ A559 

M^ AlX4- 

^16 Alio 
/I6 1B44 
Zi-6 $rtft3- 



P 65 
74 



P 10 

P OQ 



419p-iH 

4T^4-lH 

„4TJi^-3^. 

4THo^3:^ 

4Tn6-3/ 
J1TMfi-^4 



PlTo^-l3 
PlTrt-U 



P4T5C-11 

P4T^(}-1 
■.a4T4^wp. 



Jn?:^ *<EMCRY WRITE pELAY On/OFF 

?02'' HEMORY tA/B) 

g pa^ 4£K0^ Y S FO ME NrER f A/fl> 



MEM RITE 
MEMORY 
-HEM SEP 



DIG B 
DIG 8 

-nin B 



/j6 1B47 
/16 1B49 
M^ 1^^^ 



P 01 
? 01 

P 01 

n 02 

p Qg 

2 o2 



4To6*4? F4T4o*i4 
4tn2-67 P4T4g-o6 
4Ttj 4 ' -^ (j P 4T^^^ ^ 



^o3n 



A/D CONVERTER STATUS (A/81 
INALOG Mux ih/Hi 



^44 DJUUJtAL. 



U_ 



A/n CO^JV 

ANH MUX 
niG MUY 



DIG B 
DIG B 
nifi R 



/16 

/16 



1851 
0955 



41u4-67 
4Tq6-3B 



P4T4(i-7 

P4T4C-11 

P4T4G-ft 



?03? FORMATTER LOGtC STATuP A/P 
9o33 KMtR PUF AMP cTATi'S A/B 



FOPMATTR 
RUFF A^p 



DIG B 
DIG B 



/16 0^57 
/16 1853 



^To2*fr2 
4Tn6^67 



P4T4tj.53 
P4T4d-i5 



^HF TRANSMITTE*? 



9iQQ — ^FFi eriFp pnwcR 



RFFi PkR ftlOG U^ A4^fta cp ip 4Tfto"S,a 3 T[j 3 'o3 — 5714,^1 






^loi 
^irj? 



*10< 
'io5 



TRANSMITTFR A -a^ vDn Ol^TPUT 
TRANSMITTER B -2p vDc OUTPUT 

■-tRANSHlT-tFR A T-EMP-itATUiifL^ 

TRANSMITTER B TEmpERaTOHE 
KMTP A# RF POmER OiJTpuT 



XHTA-2cV ALOG 

xhtb-2(jV alog 

,XrtlR-.A-T A4^aG„ 



XMTR B T 
A RF PkR 



ALOG 
ALOG 



1/16 Ai73 C^ 1^ 
1/16 A23e 19 2** 



1/^6 



A 3* 5 
A340 



15 46 
02 43 



4T«2-53 3Tn3-a3 57i4-r,2 
4Th4-33 3To3-o9 57i4*fl3 

_:U-b6--^^ _.^^Tf^^i 57 t^*fr4^ 

4THe-53 3To3-i4 57i4-p5 
4Tee-7i 3To3*l6 5714-^6 



o 

to 

00 



DP^7J2229o2AV RFV B PRTS ELprTRICAL SYSTEH*^ SCMtMAT IC/TElEme FRY HaTpIX ^^6/^9/74 



PAGt 



le 



FUNC 



TLM FONCTlOM 



ACPONrr* . SlnML SamP .QATE column VIP S/S IKT 
TYPE SEC ' ADOR /fiOW CONN CC^^ CCk<*.= 



^10^ KMTR fl, RF POuGR nuTpuT 
'lO**' ^f^^^ff* "f^f^E A HIGM/Lnw 

>1^ ^4^Kg n D AT I I t P U T — Mft4f 

^lll 3ATA TNPmT RFALTIHE/STORFD 
9ii? »nwER HOOF P HIGM/Low v ^ 



P t*F fvR ALOG 1/^6 A4?9 iP 55 ^T^Q-bLs 

PWR MD A DtG 8 i/i6 ^Bft^ qP q3 4To6-6i 

DATA Ut DIG B i/j6 ^956 jp (j2 ^to2*?l 

PWR MD 8 Din =5 i/i6 735i iP ol ^'^04-7j 



^ARHOWBAND TApg RFCORDER NO, 1 



3Tp3'iP 57i^-n7 



I00ft3 



loon6 



^OHFR SUPPLY r'JRRCwT ^ 
^ECnwnEH TEPPFRATiiRE ^ 
aOwFR ^flpPtY uQLTftcE | 



RECORD HnOE 1 ON/OFF 
PLAYBACK H0D6 1 OMyOFF 
-^C^tfil-^MiL.^nF: T A RE Prt MAR v i Y ES /N Q 



PS Cur I 
RCnR T 1 
P*; VLT ^ 



lOO'^^ ^FCORn Fk'H OF TAPc 

SECONDARY 1 YGS/nO 
tO 0n9 aL A Y n* CK Ufci D rC T * rE 

3R|MAPY 1 YE«:/MO 
10010 PLAYBACK FNl^ of TAPE 
— ^C O N f^ Ak^f^^ Y^^/mi — 



RECORD 1 
PLAY9K 1 
R £ nT P ^ 



ALOG 
ALOG 
ALOG 



1/^6 A493 01 'J^ 4T92-5J 
1/^6 A557 0*? 74 ^T94-5.T 



-iUifi 1^^ >^^ H-« ^ ^^0"1^ 

DU e i/i6 3B38 Di 00 4Toa-o9 
DU B 1/^6 3B39 e? po 4Toe-6^ 
P t Q R 1/^^6 3^4-0 &^>-e6 4TQg-^ ii- 






5JVo3*^ 570^-13 
5N(}3-*F ^7(,9-i4 



REOT $1 DIG 8 1/16 3841 lo qO ^To2*4-t 5No3-S 57o9-i6 



PEHT P 1 DIR 8 1/^6 3B42 l? OO ^^To4-^H 5No3*T 57o9-i7 



inoll ^ECOftpER PRFS^'JHE 1 | nW/NOR 



-PE nT S 1 



RCnR p 1 



/-t^ — 3B-«---l^"i) — * T^&A^^4 
1/16 8363 1? o3 ^Tn8*iy 



5Ko3-N 57o^-l2 



lOinl 40T0R CURREKT 3 



l{lin3 ^tCOROER TEf'PFRATURE p 
lOin^ »nWFR SUPPLY vOLTAGt ? 



lOin* ^tAYPACK MODE 2 0*'/OfF 

PRIMARY 9 YE<:/NO 
lOinfl RECORD Emn flF TAPP 



MOTR I 2 

PS Cur g 



ALOG 
ALOG 



RCnR T 2 
PS VLT 2 
RECOPD e 



ALOG 

ALOG 
Dlf: B 



1/16 



PLAYSK 2 
REoT P 2 



DIG 8 
DIG B 



1/16 



Al72 
A 237 



C? 1* 

l o g fl 



4T62-15 
4TH4-ft^3 



1/1^ 
1/1* 



A^oo Ifl 37 
A3A4 1^ 46 
■^^U4 IP 00 



3845 
3846 



4Tt^6-i^ 
4186*1^ 
4T06-SH 



01 01 

0? 01 



4To6-44 
4To8-5(^ 



t>Ko4.#p 
5^()4*H 



5Kn4-*F 
^Ko^-n 



^70«-Pl 
*57o*»-'?0 

^ 7n^ 19 



57o9*33 
57o^-'^< 



3EC0NPARV 2 yES/no 
min^ PLAYBACK FWfi rf TAPE 
^flrHARY gi YE*:/ND 



REoT S 2 
PFOT P a 



DIG B 

nic R 



1/16 



3B47. DP 01 
-l^^ — lo 01 



4TO0-44 



5^o4-S 



570^-35 
57og *;i 6 



10110 PLAYBACK FND nF T*PE 
SFCOnPARy 2 vES/^'O 

10111 ^FCrftnFR PRFSSUrtF g LHtf/WflR 



PEoT S 2 
RCnfl P 2 



DIG R 
nift B 



1/16 



3349 12 01 

-iBsz — IS pa 



4T02-24 



5Ko^'V 



97o9.37 



JMtFlFD S-BANn EOMfPHFNT |USe> 



llOOl RECEIVER AGC v^ILTAGE 
llOftZ '<*^TR OUTPUT Pn^ER LEVFL 
110ft3^FCFlVER ^^TATtC BHAS^ FRRAR, 

iioo^ trawspondFR tfhpepaTupe . 



RCVR AGC 
XMTR PMR 

RC\/R FP B 



ALOG 
ALOG 
ALOG 



1/^6 
1/16 



A427 12 55 
A492 18 64 
JIS56 C^ 74 



4T9Q-3b 
4T92-15 
^ TV 4- i^ 



3t3l-N 
3U31-T 
3t.3 i* W 



57l4-,7 

97i4-^e 



TRSPOR T ALOG 1/16 Alo? 1^ o' 4T8q-3* 3i*3l-P 57l4.po 



:d 



n^47J2gg9ogAY RFV B FftTS EL ecTRICAL SYSTEMS SCmEHAT Ic/TELEMETRY H4TRU ti^^/^^flA 
TLM FU^lcTlO^^ 



FJNC 
N3. 



ACPOWYH Sir.NL . SamP GATE COlUHN VlP 
TYPE SEC ADOR /ROW CONN 



£/S 

CC^^ 



UT 
COnm 



PAGb 






o 

CO 

to 



.J 



11005 TRANSPONDFR PoESSMftE 

11006 ?FCEIVER A/P 

li o n? ^MTR ft — riM/nrr -,5V 



iiQio iiTx n^^cTn ftTni? avPA^fc/PMARt c^^ 

llOtt HODULATInM INPUT NQRhAL/CROSSED 



TRSPDR P 
REreivFR 
yWTA-iSV 



XHTB-^5V 
RNG -i5V 



^REhQnULATOR PRQCFSSnP CPNP>- 



llir2 *nwER SUPPLY p VOlTAqf 
lUoi TFHPF£lAUjaE^^ 



lirr4 TFMPERATURfc B 

llin5 3ISCRTHINAT0R A OM/OpF 



UlO^ HODULATOr A 0^^/0F^ 

llin* HODULftTOR 6 0^«/QFF 

11110 WftVTft 1/? 

lUtl ^FCORHEr? TN NDTR/WgVtP 



WIDEBAND POw£P AMPLIFIER N0» 1 
l?Ont :0I t FPTnp TFMP 1 . 



l?Or\? ^FLU CURRE^T t 
I2nfl3 :AT^*n^E ruRf^E^'T 1 
.V2fHi-4-:=^0RtiA&B_p,awEJUi 



l?gc5 REFLECTED Pnwr:R j 
l?(,n6 HEATEP STATUS 1 0*VOfF 
l?9 nfl ^DtfFR UnpF 1 HIGH /I nif^ 



^IDEBAVNn POWFR AMpLlFl IR N 



l?inl :OLLErTOR TbHn 2 
l?in2 -iFLly CnRRE^'T p 



l^tO^ *nRKAPD POWER 2 

l?10^ REFLECTED POwrR ? 

? t oft ^£ ft T ^fi^_Hjj.IUS^^„Ojj/Q^lfL- 

l?in6 ^OHER HOnF ? Mi/Lnw 



JtnFR^Mn FRFDiiPM nv HnnUr^THft 



l??no ^BV FftTER A 

^ IP ^ |__*B V -4^ -IL-T tO-E 

l?2n2 AUX. DATA TO p9V FILt. A 

l?2n3 *^*X. nATA TO PRV riLT* B 



rUT/TN 



Hon IN 



ALOG 
DIG B 

ALOG 
ALOG 

nrn r 



1/16 
1/16 



1/16 
1/16 



Ai7i 
3B5G 

A o7fi 



Al4l 
A?n4 



ei i9 



1^ 1^ 

25 23 



4Tb2-3*> 
4To4-i7 

4T&2-73 
4te4*7ft 

4Tf.6-j4 



3i3r 

3t??' 



3L5^5R*U 
3tg9-N 



S7i4.^2 



57t7-43 



S7i7. 



j;^ 



DIG e 1/46 3654 efl 02 4Tce-i7 31j?9-R S7i4^5i7 



PWP V 
-TE^ P A 



TEhP B 
D[«;Cp A 

MOnLTR A 
MOnLTR B 

mrtr slt 



ALnG 
J^LnG 



ALoG 

DIG e 

DIG B 
DIG B 

niG B 



1/^6 



wBvTr 5L 
RCnR U, 



DIG B 
DIG B 



1/16 
i/16 

1/16 
1/16 
1 / lft 



A299 
A3ft3 



X/l6 
1/16 



A426 
3B57 

3B59 
3B60 



0*^ 37 
In ^^ 



4Tb4*ib 
4Tc*6-36 

4Tftft-3^ 



3BA2 

0863 



Ip 55 4T9o-6i 
l?j 02 ^TOS-O? 

Cl 03 4To4-o'^ 
C'-? 03 4To6*o6 
CP 03 iJ^f^r.^ 



3lo5-L 

3lo5-M 



3tJn^-B 

3to--H 



57i4-:i4 



57i4-:^7 

57i^-:^fl 



Ip 03 
1? 03 



4To8-o^ 
.4To«-6^ 



3LC5-P 57l'*-^o 
3Lon^-f'9 57|4-4i 









^ ^^ ^ 1 ^J-^lfi m-fi^ A3A3 IP 43 4THft-46 iUi?-J 5;lij:,j^ 



HEl X r 1 ALOG 1/^6 A4n7 15 5? ^^'f^-At. 
CATH I i ALOG 1/^6 A47i iP 6i 47^2-^^^ 

-ijin^cj.L-1 — ALoiS 1^16 — kS^h (jpu^ niu^-t 

Rf'L PW 1 ALOG i/jA ii57A iP 7ft 4TV6"in 
HTp ST X C)1G R 1/16 g054 gP gg 4To6"3^ 

P"^ ^*n X — niG g — jx^^ — {^asifi ip pg 47^^-0 ^ 




CLTR T 2 
HElX ! 2 

c:ath T n 



ALOG 

ALOG 

Atnn 



FHO pw 2 
RFl pw 2 
~HTr ST -2- 



ALOG 

ALOG 
niG R- 



1/16 



PWP MO 2 DIG B 



1/16 A535 

1/16 A597 

.^-^6 — pH^a . 

1/16 pR6o 



A342 ifi 43. 

A'^n^ 1? 52 

-A^^2^^ 3.^^A^ 



Ci 7i 

If* 79 



4T68- 
47^0- 



13 

1^ 



4T96-5] 



0? o3 4To6-of^ 



li-25-J 
1U25-D 

lt.25-A 

1W;5-B 

^k3^=JL_ 



57i;?-a8 



S7l2-*il 

^712"'=;2 

57i2"^5 



YES/NO 
YES/NO 

yFSANO 



RBV FL A 

^Rlf FL B 



I22f>5 ^T DATA TO PBV^ FlTT. P YES/NO 

l??f>6 raPF 3 DATA Tn Hfiu FnT. A YES/NO 

i?2n9 TAPE p DATA To RBv FyiT. A YES/NO 

lt^20^ ^^f^"^' ? OATA Tr. Rev FtiT. P YES/wO 



AX To RA 
AX tn RB 
RT Tn l?A- 



DIG B 



D!G B 
DIG B 






9B54 






RT To PR DIG B 

Ti Tn RA DIG R 

T? ^ PA DIG R 

Ta J RB DIG R 



9B39 D? 00 




4To8-3:^ 
.4.T-f>e-^+^ 



4ToB-l6 
4T02-49 



<»T o4*a9 
4:n4-7V 

-^136-7^ 
4ToS-4^ 



^ W4 6-^^25 ■ 
3^^<^-01 

]W46-2l 



lVJ46-Q< 
iW46-24 



n?»47J2229Q2AY HRV 8 TRTS ELpCTPlCAL SYSTFM?? SCwEmaIIc/TElEMETRY MaTpIx ^t/^^flA 



PAGfe 



20 



FJNC 

N3« 



ACPOMYM 



I 

CO 

O' 



SUNL SamP gate CrLUrt*J VIP c/s jf^j 

TYPE SEC ADDR /POW CONN CCNK COnM 



OUT/ IN 

nijT/IN 

-A Y£S/U O^ 
e YES/NO 



lt'210 HSS FrLTFR A 

1??11 HS$ FTLTPP e 

-i:??-h g ^ ^ DA T A *.-T a-^<:3^-F f tX^ 

1?213 ^T DATA* TO H^g FTLT, 

1?214 ^T DATA** TO mSS FILj. 

iPgjS ;t riA T rt * * TO f ^ss fi l ti 

^?2^6 TAPE 1 DATA TO HSS FtiT. A YES/NO 

l?2l7 TAPE -, OATA To MS<; FpT, P YES/NQ 

I22l9 TAPE p DATA Tn HS«^ FnT, P YtS/N'O 



MSS FL A 
fSS FL B 



A 



rES/NO 
y£S/M0-. 



RT* H R 
PT** H A 



DIG 
DIG R 



DIG B 

DIG R 
-40-1 G 



l?2?0 MODULATOR A, vCO A^/A2 

ir^gPt ■ * n f) ii L ft Tnn b , \$q q R^ /Bg — ^ 

1?2?2 inOULATOR A* *FC OuT/IN 

122?3 HnOiiLATOR S, aFC Ol*T/IN 

-j^^i^y^q—^XA^-OUlplJT A NQRM^L/clJMH^Lp- 



l?a?5 DATA OUTPUT 6 ^ORHAL/SUMhFD 
123^6 ^eV BIAS Ayo 

i 7 ^O D HLftT n p A ^ j O O P s Tr ^ .?3 ; S - 



tPg ^ ^ 



l?2?d HGOUlATOr B, I OOP sTrfss 
122?9 ^BH TFHPFPATU»E 



-V- 



W8M POWER I^VFRTER 
l?g^O ^HM UIVFPTFR ft 



OFF/nM 



t?2^1 *rfBH TMVEflTER d 
1???2 15 RFG, VOLTAGE A 
-15^1J 3,5„ RF G vnLT ArE B . 



OFF/ON 



122:^4 -^5 RFG vnLTAf^E A 
i?2S5 -15 RFG VOLUrE B 



12237 5 REG VOLTAGp 8 

I22?ft -5 .REG Vn« TAGF A 

^?5JJL_*5._R€^v-J£o4.Xfi.G^^a_ 



122^0 •^24»5 MONITOR NO, ^ A/B 
122^1 •24*5 MONITOR NO. 2 A/S 
12343 rfflM IMVFRTFR TfiMP 



Ti To ^^A 
Tx' To KB 
— I^^^'-O-Xt 
T2 TO KB 
MOOA VCO 
HOnR VCO 



DIG 
DIG 






MOHA AFC 

MODS AFC 

^A T A i 



DIG B 
DIG 8 



DATA B 
R8v BIAS 
HOnA L S 



DIG R 
DIG H 

JiLnG 



1/^6 9^56 
l/l* ^B57 

l/l6 QB48 
1/16 7f5ft3 

-^r^ <^H^5- 

' 9^49 
985o 

1/16 99-55 
1/^6 996o 

t/l<^ O S ft^ 

1/^6 9^56 
l/i6 93S9 

^^^ ^1^ 

1/^6 9B4i 
1/|6 9947 

-t^4^> Ah444- 



'*T,,2-75 
4Tr?-5^ 




12 02 
15 o2 

lO 01 

12 0^ 

12 01 ^^ri2"o'' 1^4^-27 
I'j 01 *^0<'3.S 



4To2"33 
4T08-4*? 



lW46-3o 
-lfc'4^^2^^ 

lU46-2^ 

-^Vk4 ^. ■= p 7 . 



Ip 02 -^Ufi'O^ 
C? 0^ .<Tf|6-73 
oft fl3 4Tn 6 -5tf 



IP o2 ^To^-73 
CI D^ 4Tr:4-&^ 

10 00 4Tc2-7^ 
OB 01 ^^06'7V 
C 2 frl «J^ 






1U46-35 
lk'4ft-i3 



HOnB L S ALOG 1/1& A586 0** 79 41^6-45 
WBm TEPP ALOG 1/16 A33e iB 42 ^ 4Te8-44 



^^4-« ^hA t ^ ^ A 



lW4ft-33 
Ik4fi*i5 



INUHTR A niG fl tZ^ii 9^^^ t^-^^fl 4Tofi-'^^ lUn^O? '^71?-'>o 



INVRTrt* B 

i«;v A 

jSV B 



DIG 8 

ALOG 

ALOG 



-iSV A 
-l5V B 
^V A — 



5v B 
•5V A 



ALOG 
ALOG 
ALOG 



1/1* 
1/1* 



ALOG 
ALOG 

ALnR 



1/1* 
1/1* 
1/1* 



2B47 
All3 

-^-3-^3 



-24*5 ^1l 
'-24. '5 H2 



ALOG 
ALOG 
ALOG 



1/1* 
1/1* 
1/1* 



A2i2 
A339 

-nA^%* 



CP 01 

15 10 
CI gS - 



IP 24 
CI 43 

1 ^3 



4To8-l9 
4tBq-(jB 

47*?4-7i 
4Tfie-47 
4T9o^44 




1/1* 
1/1* 

1/1* 



A4n4 ce 52 4T9o-7i iUq^' 
A177 ifl i9 47^2-08 juo^- 

-A.4Afl i p fti , 4T9 g -7 _^ 54* ^^5. 

15 24 4Tfe4*47 iWo5* 
le 78 4T96-4e jWo5- 
lO 7 fl 4Tyft-72 ikii' 



OP "5712-71 
•13 ^712-72 
:-l4 — ^7t2-7,i- 

'D3 5712*74 
'04 5712-75 

-^ '^7l?^ - 76 , 



A2tl 
A59q 



12 57l?*77 
0^ ^7l2-7fl 
-^ — ^-1-2*W- 



01 "sri^-fto 

0? *57i2-fli 

■frS — ^7i g. Ra 



§p 




II 


. ' 








£f^. _ 






















^ 








i * 


* 
I3po0'l^n00-l5oo0*16000 •* 










* 












* 




























' 


* ■ 


o 

1 

CO 






. 




' 



n»47J2229o?AY HFV H FHTS ELFCTPjCAL SYSTEMS SChEhA T I C/TELEHETRY HaTrIx ot/x9/74 



^AGfc 



21 



O 
f 

w 



FUNC 

N0< 



TLM FUWCTIOM 



ACPONYft Sir»NL SamP GATE COLUMN VIP S/S IM 
TYPE SEC ADnf^ /PQW CONN CC^^ CCn^* 



WIDEBAND VIDEO TAPE RFCHRnER 1 

l3on2 ^^V STANORY i YES/NO 
I3nn3 ^ECORH 1 yES/mO 

^LAYBftCK i YEr/NQ 



-1- 



t3oo5 "AST PEWfMD j YES/NO 
l3of»^ 'AST FWD ^ YE<?/NO 
-^3on 7 ^R V -i^MA3^.E ^ V E $/ AI^ 




i^t 4^^ 



^ i^^ — ft 2 *-rC 

L7 0^ ^^i\^^ 




k^6---J 






l^oftft 'PIHAPY FMD OF TAPE ^ YES/NO 
l3or>9 5EC0NnARY E^O OF TAPp i YFS/^O 



PEuIiuD 
FOwApn 

P FOT 1 
S FOT 1 
P PflT * 



DIG B 
Din B 



OIG 6 

DIG e 
nin H 



6-*J 

6-*S 
t-*F-. 

6-N 



O Q 



13(511 SRCONHARY BFGtN of T^pE ^ YES/HO S PUT i 

I3ni2 ^*^V RUN TAPE 1 YE*5/No RBv TP i 



i3oi4 iss/pnv statuc no I hss/rbv 

I3iii5 :UHRFMT stT Tn 4Dp Nn i T^'/OUT 

i^y ^ ^ : iJ RRFhT i ; eT - To nR m p t tM/T ill T — 



i 

STATUS 

4Dp SFT 

p Q P RET 



DIG e 

DIG 8 
QIC B 



6-P 

^-*G 
6-^Rl^ 



DIG B 
DIG R 

DU R 






§1 






13017 
1301» 



i3n?n 

l3o?l 



:URHFNT RPT To 1 Pfl MP t TN/OUT 
SOMVEPTEr PPImAHY PWr 1 o*y/oFF 

ViiLTAnE-Pcn.T-erJt^^-FtUiiCE^aiSAflLE 

»niHAPY vnLTArE RanUf NP ^ IN/OuT 
i/OLTaHE pROTErT RFLAy t QPEN^CLOSED 



|.^f^^2 ru Pprq^iiiDt: ^ 



iDp set 

CNV PWP 
_UU_pRX 

P V RNG 
V PR RY 
Hi PPS 



DIG B 
DIG B 

-D-in_B- 

DIG 9 
DIG R 
ALOG 



6s.T_ 

^•#P 

6-S 

^>*A 



l3f)?3 
l3o^4 



TU TEMPEHATtlftF ^ 

= U TE^-PERATURF ^ 

^3^f^;jS TAPF FQOTAGl^ ^ 



l3nP6 
130?^ 



JAPSTAN MnTO« SPEPD i 

HUP MPTOH SPEfQ 1 
CAPSTAN wnTfltf nimffENT t 



TU TEMP 

Fu Temp 

TAPE FT 



CPST HS 
HWP MS 
XftfJ— ti4- 



ALOG 

aldg 

ALOG 



6'*P 
6-C 



^LOG 
ALPG 

ALDG 



6-e 



13(j3q 



PLAYBACK VOLTAGE ^ 
4Wp HPTOR CURRENT NO i 
4£CnflJ)ER 4-UPUr HUPRFaiT 1 



P/o V 1 

HMP HI 

-B_IJN_J- 



ALPG 
ALOG 
ALOG- 



6-H 



*C- 



l3r).^2 .IHITPR VOLTAnE No l 
l3o33 SERVO VOLTAGE NO i 
t.^034 :ONVERTFp oniPjT 5>AV 



LMTR V 
SERV V 
*5.ftCNV 



ALPS 
ALOG 
At Ofl 



6-D 

t-F 



WlDEfiANO VIDEP TAPE RECORDER NO 2 



13101 '^SS STANDflY 2 YES/NO 
l3in2 ^RV STANORY 2 TES/NO 
I'^ltl^ aprnon ^ v^gy^.n 



MS<; SBY2 DIG 8 i/i 6S37 16 ^4 4to6-4? &y4n-*R 

RBy SPY2 DIG R l/j 8635 16 q3 4Tt)4-3l 5W4o-*n 

UR ftpn a — DIG R 1^4,. 8-^ 5ft a? q3 4TtjA*'Ti 'afclflp-^H 

WB PBK 2 DIG 8 1/^ 6837 16 q4 4To6-3l aU4o-*l 

REwlMD 2 DIG 9 I/16 4853 C2 o2 4To6-69 i>M4o'*J 



l3io^ PLAYBACK YE^/NO 
l3lfj5 ?AST PEWTND 2 YES/nO 



nP47J2?29o2AY RfV 9 fRTS ElECTRfCAL SYS.TBM*? SCMEmAT 1 C/TELEmETRY MATplX ^t/x9/7A 



NO* 



TLM FUmcTJO^ 



ACRONYM SIGNL SamP GATE COLUMN VIP S/£ - IM 
TYPE SEC ADDR /POW CCfgN CC^^ CC\'^' 



PAGt 



?2 



3in6 "AST FORWARD p YES/No 

.^in7 ^RV FMARt^F ? vES/MO 

^f>6— gRXMA-aJT— ^n QF TAP.^-p^£<v/J^lQ- 



3lft^ SECOwnARY END OF TAPF 
3iu) »RIHAPY ftFG!N OF TAPf 2 



3ii2 ^HV RMN JAPt p YES/Nn 
3ii3 *AP NO 2 YES/wO 

^ 1^ ^_^aS/RPV ^TlAJXtq^^ „ 

3ii5 JimPpMT 5;PT A HH ? 1m/0UT 
3ii6 :URHE^'T fcPT Z HH p U/OUT 
i^^7 rllRRP^a g<=r ^ ntf ^u.^miT 



YFS/NO 
YFS/NO 
y YFS/NO 



FOwApD 2 
RBv EN 2 
-B-J^OT g 



Din 
oin 



POT 
POT 

priT 



Din 

DIG 

nif; 



l/l6 



H^^J^/PflV 



HBV IP 
LAP 2 
STATU? 



3tlfi :niV(VERT€R PRI^'ARV pWp 2 flN/OFF CNV 

;ili9 ^/riLTAnE pRniErT 2 EN/nis vlt 

■3^.;iQ— JP4ilARY^VJ1Lt,^JtAAinE NO 2 TN/ODT £ 

3i;?l ^/OLTaOE PROTErT RFlAy 2 OPEN/CLOSFO V 
3tP2 rU PRFSSijDE 2 TU 

atP3 FN TEHB£jjATIiRF g Hi 



4DPI' 
2Dn 
iPR sFTg^ 



2 Dir, 
Die, 

2 ai-G- 

SET2 Dir, 
SE12 tJlr, 



1/16 

t/16 



PWF2 
PRT2 



Din 
Din 



B 1/-1 
B 1/16 * 

9 1/16 



4S>j4 oP 02 
9B34 17 02 

4S56 12 02 
4357 35 02 
^RSfl IR 03 




bU4o"*S 
bW4o-*F 

!^V^4o-*F 

r>Wdn*P 



9B35 
4959 



1/16 



4362 
.4fiAj j^ 



6939 
6939 



If 03 

01 0^ 



4]u4-i^ 

4To4-3f 
..4.U6--^_ 
4To6-3f^ 
4X06-35 
4Tfia-3ft 






3t?4 rU TEmPFrATUP*^ 2 
.^?5 rAptf FOOTAGP p 
3^^A^„: APS T Ali^tiaTJia_3fi£F-li-^ 
319? HHP MOTOR SPRrO p 
3128 :APSTAN MnTHR CURRENT 
3ip9 JI.AYRACK vni TAnF p 



PR RY2 Om S 1/^6 6tJ4l lo 
PRS 2 ^LnG 1/^6 AiQ5 ip 
tfM^ iLUUG l/^lS ^LJ^9 3_p 



CI 00 

C2 on 



3130 HWP MnTOR COPPcNT 2 

3131 ^FCOROER INPUT CUPREmT 2 

il^^2-,lM.lTFR. VflLXAaE^ 2^ 

3i33 SEftVQ VOlTAGE 2 

3i34 :ONVeflTER OUTPUT ?.^v Nn 



FU TFI^F2 
TAPE FT2 
rP^J-,H^-^ 
HWP HS 2 
CP*;T Hl2 
P/R V p 



ALOG 
ALnG 

AtnG 

ALOG 

ALnn 



1/^6 
1/16 



00 
22 



4Toe'-3? 

4Toe-47 

4Tn2-2^ 
Alb4'6fi 

4Thft-6^ 



5W40-V 



5V<4fi-*P 
&h4o-T 



bVJ4o-S 
5W4q'*A 



HWP Hi 

f< IN I 



SERV V 
5,6CNV2 



-e ALOG 
2 ALnG 

„2-~ALnG- 
2 AldG 

ALnG 



A3?2 1? 4o 

A3fi7 le 49 

1/16 A5t4 ci 6B 

1/16 A5q4 lo 79 

1/4^ A-&^-Z CP ^ 

1/16 A131 OP 13 

1/1 A63o 09 o4 

%/^t — M^JS^ 3^-22- 

1/^6 A26i IP 31 

1/16 A463 1? 60 



4Tbe-25 
^l9o-6^ 

-4T9g-.&a- 



4TV4-2^ 
4T96-44 

4THn>AK 






6W4p-G 
fiW4n-E 



4Ta2'^^ 

4196-55 

41*^6-14 
4T92-49 



5W4Q-H 

&W40-F 
^1^4o-K 



92 












^ 



^Rv cahera co^ fro* lEr 



J,4.^.,^^_lALlBaAj£^-Lh!AQL£vJlX5ARL£_ 



O 

I 

CO 
CO 



l4oni -CC flnAKH TFmpERATIjHf 
l4on2 3CC PnWER Sl'PPLY TEMPFR^TMRE 
-jJi^^ ?l IIS nR MiNifS 1? VQi T SitpPLY 



l4of)4 ft* -S.2^ VOLT SUPPLY 
l4(jf>5 APERTURE rORHPCTOR OuT/lN^ 
^,4fH*6-^:^tL£ rOMT/^Jyfi 

i4on7 iXPosMRE r pn/off 

l40n« EXPOSURE a ON/OFF 
-I4^n9 SXPQSHRE B Ghi^uEE \ 



14010 1-6 MHZ CLOCK ON/OFF 
1^01 1 H0Rl7nNTAL SYf'C ON/Opr 

l4ot3 iHZ SYNC ON/OFF 



CktlBSAX AUlG 1J4^ tZ^A ^B—A-^ 4Tefl-7o 3&l^--^^ 



CCC BD T 
CCr PS T 
l5v SPLY 



ALnG 
ALnG 
ALOG 



1/16 
1/16 



A368 
A452 



01 5(1 



4[9(^ 
4T92-70 



6-5. 25V 
APT CORR 



EXPOSR 
FXPOSR 

f XPfJpR 



1*AHH2 
HOP SYNC 
VFP SY^C 



ALOG 1/^6 
DIG B 1/16 

OIG B 1/16 
910 8 1/16 

nm a — i/^ft 



V^-ti A^t5 CP 1^^ 4T94-A^ 



;sfii4-i5 

3Pn2-oi ^^lo-'^ 



^^^ 



A593 oP 79 4TV6-2^ 
6042 J2 00 4T04-75 
.tR 4 3_lS~^o — ^"^^^4 - 2iJL_ 
2^57 15 o2 4Tfi2-22 
6^345 01 01 4To6-25 



3Ro3-o4 
3Pl4-o^ 



3Ri4-o5 
7^1^-0*5 



DIG P 1/^6 
DT6 B 1/16 
D I G B 1/^ 6 



MU6 2 01 4Tn a -7^ 3Pi d -in 



6947 oP 01 
6648 lo 01 
-6345 a-p-^H^ 



47o8-25 

4Tq2-52 

-4X^2=L^- 



3R14-11 
3fii4n? 
^ ^ 14 -13 - 



57io*Z&^ 



5710-77 



lH7 SYNC DIG B l/i6 fiB^l IP oi 4To4*2t) 3Rl4-i4 



E>*47J2229o?AV Rf^V 8 F»^TS ELPCTPICAL SYSTEHS SCwEhAT Ic/TElEhETRIT MaTrIX o^^l^'^^ 



I FJNC 

to HO* 



TLH rUNfTllOw 



PAGt 



ACffONYH SIGNL SAMP GATE COLUMN VIP ^/C i^j 
TYPE SEC ADOR /ftoW CGnN cC^^ CCnm 



?3 



1^014 -24*5 VOl.T INPUT ON/nFF 
l4nl5 :CC POWER O^/OFF 

^TiE-j^A CTTV ^ TTO N oN/OFF 



-24V U' 

CCC PWP 

^ T M PE A C 



DIG R 

nir, B 
QI C a 



l/l6 
l/l6 



6352 01 02 4Tn6-52 3Pr:;-o? s?!©-?** 
6053 0? 02 4Tu6-26 3Rc3-o5 5710-79 
6B 9 4 ** o a *^<>^^^? j p ^ ^ ^ ^fl 



^BV CAHERA 1 



l4ino VIDEO OUTPUT ^ 
l4lnl 'OCUS CUpRE**T 1 



l4in3 TFMPFRAT»IPE E»€CTPONrnS ^ 

l4io4 TFHPEPATMPE LO^-VOLTaoE pwR SUPPLY 



Ili f | 9 J r FL E rTlnM PQn g R SUPp i Y ^ 



Vln OUTl 

FOr I 1 

ELPC T 
LVpS T 
OFT P fi 



l4iri6 
I4in9 



.nw vnLTA<lE POrfGR SUPPLY -I 

THEPMOELFCTRir UNIT cnRPF^^T 1 

I U^H^^^A^t^H X C UHfrPJO-^ 

3t VOtTAOiF 1 
TARGET Vni TAOF t 



LV PWS 
THmO 1 
VFTL 1 



■ V IDI CON Q A THg rL g . CURriF f^i T | 



Gi VLT 
TGT V 5 
VCTH T 



I4ii2 ^npl70NTAL DErLECTlOiJ OUTPUT i 
14^13 ^FRTlfAL ^EFLFCTTnN OUTPUT 1 

-^^^4^|^-btPF4mX^Jft fe FJiC6P > A T g ^ 

I4it5 TFMPERAThpE YoKE/FOCnS CotL 1 
l4j^l6 .?4.?V PnvjER T^ NO. ^ ON/OFF 

^4^|7 .p R i/ni T QHilTTPfl rtlRorMT ^ nN/flFF 



HOR PEF 
VEP DEP 
-XPlT T 



y/fc t 

-24 IN 



ALOG 

ALOG 

ALOG 
ALOG 
ALn C 



l/l6 

l/l6 

l/l6 
1/^6 



Ao6e 

Ax32 

-A^i^a- 

A2ft2 
A325 



In i3 



Cl 32 

ci 41 



4Tao-7o 

4TH2-7p 



ALOG 
ALOG 
AcnG 



1/t^ — «^« — fr^-5-e — ^^^n-'i 



ALOG 
ALOG 

. ALOG 



1/^6 
l/l6 



4TH6-75 
4166*14 



_^ ^^ f. r /J i_ 
2Pc^-05 



A4^3 
A5i6 



ALOG 
ALOG 
A LO G 



1/1^ 
1/^6 



Ao69 
Ai33 

Al 39 






ALOG 

DIR B 
D I G R 



l/l6 
l/l6 



A2'>3 
A326 



lO 04 
IP l3 

C3 P3 




i-PO^^lO 

?Pn-"o3 

tFne-o3 



57o^-r2 



^Pr'^-li *57o'*'p3 



Kft fi* i 



l/l6 
l/l6 



A454 
6B56 



0? 32 

0? 41 

in 59 

IP n2 

1 ^ 00 



4TH6-2r^ 
"4Tfcte-7*5 
-4l5.Q-7^- 
4192*75 
4U2-5S 

4Toa-ftn 



t^Rn^-04 

5fiC?-05 

?fio^'0^ 

? B f/-l^ 



S 7 d P - 
*57o**-o5 



l4l?D 5oo VOLT<i 1 O^/OFF 
_aBii,XAWEflJL-2 ^ 



5nOV 1 ALOG l/i6 A197 15 22 4T64'-i4 v^R^^r-n^ 57o'*-10 



O O 



.*T? Q 






^ 






l42oO ^IDEO OUTPUT p 
^42nl "^^"S ruppFHT o 



vm OiiT2 



ALoG 
■ Atnfi 



l/l6 



A5i7 



l42n2 :nME'rNED fiLIG* ^ENT CiirRFnT 2 ALnN I 2 A^nG i/i6 Aq^O 
l42n3 TFHPEPATmrE. FLGCTROMtCS ? ELEC T ? ALOG i/i6 Al35 
^A^pj TPMPt:PATiiPt:. I 0^ \fnLTM;p PWR SUP o 1 VPS T g AUlG 1^.^^ A^-ft4r- 



10 6» 



4T94*l4 
4T<vfe-40 



l42n5 DFFLErTIn^t PQi-^Erf *5mPpi Y NO 2 
l42n* -"^^ VOLTAf;E PnWER SUPPLY ?> 



OFi. PS 
LV PkS 
THmQ 1 



1? 0** 
IP l3 



4T8(j-7ti 
4Trt2-2H 



3P24- 



3F24- 

3F24, 



01 
0^ 



l42nB ^TOICON FRAHFNT CURRFNT p 

l42n^ ^1 V"» ^*GF 2 

l4aio TARGgT Vol TAGF NO ^ 



VFiL I 2 
Gi VLT 2 
TGT V 2 



ALOG 1/^6 A?^6 12 3? 4T*^6-4'> 
ALOG i/i6 A327 o^ 4i 4ToB-2^- 
AioG i/i6 A39i iQ 5o 4TVo*2^ 



3P?<' 



1? 
ir» 



AL'lG 
ALOG 
At.nG 



14211 VIDICPN CATHOr^E Ci^rRf^T NO 2 VCTH I 2 

l42i2 •(Ofll7nNTAL nEFLECTlOw OUTPUT 2 HOP DFF2 

^4o^l JFRTTTAi OFFtCCTInM ntlTPHT y VER TIFFg 



ALOG 
ALOG 

ftl OG 



l/l6 
l/l6 



A455 
A5tB 



l/l6 
1/^6 



A0^2 
Ai36 

^ 2f}2 



JP 59 
12 <^3 



4T92-2^ 
4T94-7'? 



5Ri?' 



14914 rEHPEPATURE, FACFPLAtP 2 FPlT T. 2 ^LOG 1/^6 A268 
X4pt5 TEMPERATURE* yOKE/FOCmS CnlL 2 Y/fC T 2 *LOG 1/46 A329 

|42l* -g^'^v PntfPR TN- hQ^^ ON/QFF * 2tf IN g — niR B — %l^ — tfiAfl^ 



IP 0^ ^THq-i? 5Pi 
CI l4 ^Ta2-i2 ^fi^ 
ip ?3 4Th4-4'? ii£4 



02 •>7o<'-p4 

03 570^-25 
^4 57*2^^ 



I42i7 n^B VOLT SHUTTER CMRrFNT 9 ON/OFF SHTR I 2 DIG 8 t*/i 4832 

l422o 5oo VOLTS 2 O^i/OFF 5r)0V 2 ALOG I/16 A26o 



16 32 

12 41 

14 00 

15 31 



4Te6-76 
4Tft8-2^ 
4Tofi*'a'j 



01 57o'*-:>7 
^fil^-O* S7of»-98 

'jFlfi'o'^ — '^7nP*n9 



5fiie-i4 57oe-:^o 
" -0^ 57ofl-;^i 



4To2-1 
4Tfi6*7o 



5Pif' 



;SP24 

5Rie 



^^ 



'li 

'oP 



57o'^-:'3 



0f>47J222902AY RFV B FllTS EUFCTRrCAL SySTEM<: SCHEMA! lC/TEI,tMETRY MaTrIX od/^9/7^ 



FJNC 

NO* 



TLH FUNfTIOM 



ACPOnYP^ SlGNL SamP GATE COLUMN VIP 
TYPE SEC ADDR /POW * CONN 



S/S 

co^^ 



INT 

cc^J^1 



PAGt 



?4 



O 

I 

w 

en 



^eV CAMERA 3 



l43oO i/IDEo OHTPtJT :t 
l43nl *OCU<; CURRE^'T 3 



l43o3 
l<3n4 



tfhpehatijpe* 
temperature* 

-JQIJEH SII PPI Y 



FLECTROnICS 
I aw VOlTAGF 



vin 0UT3 

For I 3 



ALnG 1/^6 
ALOG 1/^6 
At nG 1/16 



A392 
A457 



1? 5o 
IP 59 



4T9q.^1? 

4T9-)-26 



3P4c-o4 



ELFC T 3 ALOG 1/^6 4576 c? 77 4796-2^ 3P4o-o5 



l43n5 DFFLF^TIO^* POt'ER !^(JPP1 Y 3 
l43o6 -^W VOLTAnE Pn^ER SUpPLY :^ 
-4 4ln7 THFRMnF LF nTRTr Hmtt nnapcMy 



J VPS T 



l^^pS ^tDICON FTLAHF^T CURRFNT 

I43n9 jt VOLTAgp ^*0 3 

l43il VIDICON HATHOnE CURRFmT 3 

14312 HnRl7nNTAI ntrLECTlON OUTPUT 

^4A,X4:< .jFnUrAi pFrtmTTnM nnTPllT 3 



Bfl PS 
LV PhS 
THyf] \ 



VFTL I 
Gl VLT 
TGT .U^ 



AtnG 
AtnG 
ALflfi 



ALOG 

ALOG 
Al nG- 



1/1^ A137 



lH3i4 TEMPERATURE, faCEPLAtp 3 ■ 
I43t5 TEMPEPATuRE, vOKE/FOCiiS COlL 3 

_tA4+6 =24^ S.V_pimE R^ IK^mO-^ qN/nFF- - 

l43i7 -28 VOLT ^HhTTew tuRrfnT :i ON/OFF 
1^3?0 ^00 \/OLTS 3 nN/OFF 



VCTH I 3 

HOP nEF3 
VFR DF'r3 



FPlT T 3 
Y/FC T 3 



ALnG 

ALOG 



1^1^ A331 

1/16 A394 

JLJ^t AiaB_ 



IP ^3 4Tt4- 
Ci 3.-^ 4THft- 



^^ 



2b 
7? 
2X- 



SHTR I 3 
^nov 3 



ALOG 
ALOG 

Pin B 



1/16 A579 
-ir^^^i /^074 



1^ 41 41^6 
Cj i^O AT-9^-- 



7^ 
4^ 
A3... 



-3R4.e 

^R4o 
3P4c 



Din H 

ALOG 



1/16 A136 

5^1 71^32 
1^16 A323 



Qj ^9 4194- 
CP 77 4T^6- 






^f;jP' 
5R?^. 

bF?P- 
bR?e* 



-07_ 

•in 



GB i4 AJ62- 

IP ?3 4TK4' 

Dj Qft — ^i^ 

:4 00 4Tfj2- 

15 40 4Tf^e' 



44 
73 



77 

6e 



HULTISPECTRAL SCANNER 
-1>(H^?--*A4^_.lJVVFRTFR^/8„. 



bF;:e- 
5R:7S- 

^R4^e' 

3^40* 



0? '^7n'?-,'^4 
fl3 570^-35 

01 57n^-37 

-f>5 — ^7n'' -; i^ 



14 *57n*5-4o 
oft 57o^-n 

.^K 

13 



l^onJ 3AND T HIGH VOUTAHE A/B 
lt>oa4 5AND p HlDH VOLTARE A/B 
I'^ O nS 3 AN n IT Hi n H Vn L T Ar E A/B 



--HA i N I^V 01 G^ e i /1 6 



l*>(jo^ -^JGH vOLTAGF: PN/OFF 

l5go7 3^MD 1 HfOH VnLTA^E n^)/OFF 

l^On' 3ANU ,? Hir,H vnLTAriE n^/OFF 

l^oiQ 3^*^^ 1 LOM VOr fAGP' On/OFf 

l^f^^X ^ANn p f n ij ivni TAcc nM^n rp 



HVi SLCT 
HVp SLCT 
HV3 PICT 



H! VOLT 
BNn 1 Mtf 



DIG B 

DIQ R 
tur, B 



1^012 5AN0 3 LOU VOl TftGf^ On/OFF 
l5oi3 3*ND 4 LOW VO1 TAGF Om/OFf 

1^015 rALiBRATlON LAiP A/B 
l5gi6 JALIBPATroN LAiP nN/riFF 

1*^01^ ^PAL MnMjTnp nM/n^p 

1^018 3AND 1 GAIN HIGH/LOW 
l5fli9 3AND 2 GAIN HIGH/LOW 
15 q ?0 .R O T A TIN G SHUTTER O U/Qtf 



bNO 3 HV 

PNn 1 LV 



DIG R 
DIG 6 

-DtG— &- 
Dir, B 

niG e 
niG R 



1/16 
1/16 



8Nn 3 LV 
PNn 4 LV 
P*iin S LV 



CLMP SLT 
CA», LAkP 



OIG B 1/16 
DIG B 1/16 

-Hir^* B j/jft 



8B43 15 00 

Pf^44 IP 00 

-JU14S C j Dl 

aB46 c? 01 

fl847 0^ 01 

^ . "^^4fi H-^ 

1/16 8B49 i? 01 

1/lA 6B5o If: 01 

i-i^A — ^^^4 — a>^ n 



^04*^^ ^*'V^-fl?- 



1/16 
1/16 



4To4-4 
4T(,6-27 

47[ IS ^4 



DIR B 
DIG B 
niG R 



PNP 1 GN 

BNn 2 GN 

-ROT SHTR 



DIG 8 
DIG B 
DIG R 



i/16 
1/16 



8^353 0? 02 

8B*54 gP o2 

«A9^2 15 oa 



41,16-27 
4To8-4 

4Tij2-3n 
4To4-5o 

^T0 4 -30 



5VC?-04 



1/16 

1/16 

-iXi^ 



P956 1? 02 
fif*57 15 02 



'^Tfifi-Sn 

4Tn8-5o 
4Tog*7 ^ 



5fn?-o^ 

^^n7-o7 

^Vn7-o9 
^^'07-10 



fiB59 CI 03 

8660 0? o3 

^4lB^i CP o3 



4To?-ei 

4Tii2-i? 

4Ttrt-ei 



bKn7-i? 

5Mo7m3 
-&|£.(^14^ 



4Tp4-i2 
4To6-ei 

41 Q t ' ^:^ 






5r'o7-ie 



^ GEL 



^£3 



I 

,.co 



np^7ja2a9n2AY rfv b frts etFCTRicAt SYstTens scmEmatic/telEmetry matru 0^/^9/74 



PAGfc 



?5 



FJMC 

NO* 



TLM FUNrTIOM 



ACRONY>= SIGNL SamP GATE COLUMN VIP 
TYPE SEC aDDR /ROW C^hU 



S/£ 

CC^^ 



IKT 

CdNM 



A/p 



l^opj 3HUTTFR MONITn*^ SOUKCF 

l5o?9 iUX MnDE <;tatiiS cphPrfs/linear 
iS^ilO ^ID SCAN cone OFF/ON 



SHTh f^ON 
HUlTPLXR 






1^036 



SCANNER POWER LINE 1/p 
SCAN' MHpnR Ot'/OFF 

aanfi pn.jFR lInf j vES/t^O 

SCAf^* MIMROR pnwER UltgF ? yES/NO 
30AN MIRROR MOOE ^'ORHAL/INHIBIT 
iCftfU WlRfTQP pliR LTNF t/g > 



HUy HOPE 

Min SCAN 
■SCH RRC£. 



SC^K^R P|_ 
SCn HTPR 



DIG 8 l/i^ 
DIR B 1/^6 

DIG 8 1/^6 
DIG R i/|6 
L UG B 1/^6 



5H43 



7B5e 






:^- 4 T t^>6^4 

(J? 4T(i4-7f> 



l5o39 SVSTfM ON-OfF STATUS nORm/OVRD 

i5(,4t) ^t>x -/^v G.p. oowFR Supply 

H^.^AXD_CaNVF^.XJ^ft.„Ri:F SHpPLY 

1*>042 ^VEPAT'E OPNSlTY OF 
SATA TRA^jSlTIn^S 

lirU OPTTCS nLATr ^ TEHnrRATURC 
"IBER OPTTCS PLATP 2 TEMpFftATURE 
HMX TFMPFRATUpE 



SCMH 
SCMM 
SHPL 



PL2 
MPE 



SYc 

MUY 



rtat 



DIG B 1/16 5B42 J2 OO ^^04-1^ 
Din P 1/^6 5B39 

-4UG -B ^^i^^^^^B^^ 

Din ft i/i6 7B6q 
DIG B j/16 5845 

n i G B — ixjA — gp^is 



in 03 4706-**: b^'o^-?! 

5Ko7-3? 

5t'07-24 



00 V . X 

C? 00 ^^ofl'2^ 

-^^.-^j^ 4j:fr6. s 4^ 

CP 03 ^Tcft'7^ 



DIG B 
ALOG 



1/16 
1/16 



9B53 t? 

A?7o Q2 
-A5>2 01- 



03 
c y 1 — ^ ^o fl 'i^ ^ > ^r?-35 



02 4^1*6-0^ 

3vS 4T^6'4^ 
-4-2 fXfi Qr7h. 



5^'07•^3 
^^0£^01 



-^*^^^03- 



1^044 

l5n^5 

l5r)47 anwEP SUPPLIED temperaturf 

1^049 ^CAN MIRRTR REGULATOR TEmP 



AVG DEKS 
FOpT j T 
FOPT 2 T 
HUV TFP'P 
:VR-1^ 

p «jply t 

SM *<FG T 
SUnH F T 



alog 



ALOG 
ALOG 

ALOG 

ALOG 
ALOG 



1^16 



-i. ^rt 4 9- ^PAW MltfPntf ORTtfF CICrrPnMir^ TCmP 

l5f55o 3GAN MiRpOR DRIVE C0j\ TpRP SMPR CW ALOG 

l5pSi SCAN MiP[^nR Tr^PER^TijpF SCw f'R T ALHG 

-1>^S 3_5IUA3U ALG^Sii U TX£H ^ti qii*; 1 hJG T£HP PS n uq T ALOG 

t5o53 3CAN MIRRHR RpQULATGn VOj TAGE SM HEG V ALOG 

l9o54 :ALieRATTON Ih^? OuRrFNT CAlAmP I ALOG 



1/16 
1/16 

^1 
1/16 

1/16 



A395 



1/16 
1/16 



A522 
A5»o 

A139 
A2o6 

Ag 7i 



CI 



1/16 



10 

If* 

01 

A333 02 

A396 t? 

-JU^i^ ^5- 



5l -IT^o-7;^ 

69 4TV4-4'? 
77 .4X^6*70 



4fc2"0^ 



A523 

A5Bi 



oe 
1? 



^f'os-o'^ 

-5^1 t*0^ 

^Mi-oft 

42 4THe-73 5^'ii-i,i 
5l 4T9n-7^ ^^'ilMl 

j;a 4T9 6 '7 5 ?iK^_^.-H- 

69 4T94-72 b 



-(^^-4Xiio^7^^ 
^4 4X^2-7? 
24 4Tt^4-4H 

-M 4Thft*49 



77 4T96- 



•'11-34 
^i'll-l^ 



l5o*i6 



15q57 
iSoM 



l5 VDH REGULATOR 
9AND 2 PlhS AmD MTNUs 

ts v.nr Rt^GihATOH 



3AND :5 PlmS Ami) MtNU<? 
l5 VDC REnUlATOR 
^AKin ^ P^ tig Afcin iJTtjiin 



BNOl i5V ALOG 1/^6 
PNng ^gy — 44.00 ^/^ft 



A076 lo 0^ 4T3(j-7t 5kii*i4 
Al 4 o — ar?"!'^ 4Tfigr J^ fi^ti-i^ 



eNn3 i5V ALOG 1/16 A2o7 02 24 4X84-49 ^Kn-if 



l5 VDC REGULATOR 
l5o«i9 .-^5 Tl M REGULATED vOj TAGF 



l^O^l ^ VDC LOGIC PEGUI AToP 
l^o^a l9 vnc RECTIFIER OUTPUT 



15064 4IGH VOLTAGE hONITOH PANn 

15065 4IGH VOLTAGE MONITOR PANq 



(A> 

(6) 

-XAJL 



BNP4 i5V ALOG 1/^6 A272 jp 

TLM .35V ALOG i/jfe A334 tjP 

— ITt'ftVPn *t.Ofi I/ 1& A?<? 7 ^ 

LOGIC 5V ALOG 1/^6 A46i in 

RECT i9V ALOG ^/^b A5a4 in 

PFrT-i9V 4Lni3 1/^6 Aqftt ^fl 



BNni 
BNni 



MVA 
HV6 
HltJL 



ALOG 
ALOG 
ALOG 



1/16 
1/1* 



Ao77 

A142 
A2Qfl 



33 
42 

60 
69 



4X86-04 

4X*^8-4r^ 

4X9o-7Ji- 

4X92-73 

4X94-76 

4T9fe-gQ 



^Kii-i7 
^^'ll-l? 



1? 

IP 



4Tt*|,*73 
^4 4T'52-4e 
^ 47^4-o4 



5H11-20 
^^11-21 



5»'ll-23 
5^11-24 



Op 






t)?47J222<>02AY HFV p Fi^TS eLPCTRTCAL SYSTEH5^ PCHEp AT Ic/Tt LEmETR Y HaTrIX (,6/^9/7^ 



NO* 



TLH FUNcTlOM 



ACRONYM Slf^NL Sam^ GATE CHlUHN VIP S/S 
TYPE SEC aODR /PDW conn CC^^ 



IKT 

ccnw 



PAGfc 



?6 



l5o^7 HlRH.VULTAne MONITOR PANn 2 iB) BHP.2 ^^B 
15,368 HIRM WOLT^GF MONITOR pAMn 3 (A> PNn3 HVA 



l^O^O 3HUTTFR MnlOR CONTHd 
INT*:fi»AT0R OUTPUT 

1^1)71 ^nA^' MiRRnft npWF n nrK 



t5(j72 3AMD SA fi* U' P!T 1 i/^ 

15q73 3AND «SA gAIK* PIT ? i/^^ 

-j5 q7j*_.,34WD .^iLJlA IK' rT T -^ ]^ /p 



1^q75 3AND '^R RAlK oIT -| l/p 
1^0-^* 3AND ijB ^AI^ PIT 7 1/fi 
1^077 3 ANn SR n fl l^ PIT 3-^3^<^ 



15qP3 door motor POwER ON/oFF 
l5Qfl4 DHOP DIRECTIOm OPFN/Cf OSE 
^5 f^l^ S-^ai) OR JiOV. 4-^.G-Y tS./:wn ^-™- 



t5oH6 DOOR HOLD OM/nFF 
XvfjR? DOOR CLOqfD YFS/NO 

|S(^ftft :)nnp nMTr;At^ Ytr</^;n 



l50«9 DOOR nPFw YFS/MO 
l5(,9o DOOR nVFpRlCE RESpT/ACTUATE 
^U9t- OnoR.^V-tftlUM-Si^-Mj^M.„_„_^ 
DUT6AS HFiTfcR ON/nfF 
HN 1 SCANNER V I D^O nUTPuT 



I5in3 



:hn 3 SCAMNfcR ViriFO nnTPiJT 

:hn 4 scA^'NtR \/iDPo ni^TPia 



l^in* "^*^ * SCAMNI^R VlllFO O^'TPUT 
l^tn^ 3MN 7 SCAMNFR VIDFO OtlTPUT 






:HN 9 SCAMNfR Vin^O nuTPUT 

:hn If, ??cankeq vinpo nUTPi^T 

:hN ^p *>rANNEc VIHFO oUTpnT 

:hn j3 SCANNER VTHEO OUTPUT 

:hN i4 SrANNFff tflOFQ OUTpilT 



I'^U^ -HN 1^ SCANNEP VIHEO nUTPUT 



ALOG 1/^6 A273 

ALHG 1/^6 A335 

-ALQfi U^jh A 39 



IP 33 4T66-?7 
IQ 4^ 4Tti6-4^ 
Si 4T9f. -4A^ 






SHTR MCI 



ALOG 
Ai nR 



&A Gn Pi 

5A Gfy Fg 



5B Gv t*i 
5B Gk^ Fg 

^R nv Pj 



niG. 

010: 

010, 
DIG. 

nin. 



1/16 



A4A2 
A^g5^ 



8 1/16 jQ*>5 

e 1/16 2^^^^ 



1? ^n 



4T94-7a 



PR ttTR 
DR OlR 



DR HpLT 
PR ClSO 
ffR OTGS. 



DIG. 
DIG. 

niG, 
DIG. 

nin. 



B 1/^^ 2059 
e 1/^6 6959 
R 1/^6 7BSS_ 



1(1 n2 
10 02 

"ieH-&^ 



4To6-67 

4T|,8-io 



^►'11-29 
" ■ ^n-37 



PR OPFr 
DR OVPP 



OTnS HTR 
CHi SVO 
CHp <?VP 



niG* 
DIG. 

nin. 



B 1/^6 
B 1/1^ 
B^-lVi- 
8 1/16 
8 1/16 



3^52 
ft35o 



H 03 
C1 fit 



4To^-22 
4To4*7j. 



DIG. 
ALOG 
ALOfi 



B 1/16 
B 1/16 



6fi39 
pf^ 4 o 



CI 02 
15 01 



4Tn6-i7 
4To4-43 



e>fo^-4o 

^K07-4i 



CH3 svn 

CH4 SVC 
CHS SV-0- 

svo 



CHf 

rH7 

PHP svr 



CHQ svr 

CHiQ svo 

CH^i <^^/0 



ALnG 
ALPG 

ALOG 
ALOG 



CHi2 SVO 
CH^3 SVO 
CH^i SWD 



AlhG 
ALOG 
ALOfi 



2842 
7U57 
6B62- 
a 1/16 3H'i3 
1/16 A079 

1/16 Ao^l 

1/16 A0^2 

^716 — AoB^ 

1/16 Aaa4 

U\^ Al43 



0? d3 
0? 00 
CP 00 



4T.,6-21 

4Tne'3i 

4T03-5? 



5^'^7-3fi 



1? 00 



1? 03 
1«^ 0^ 

o a o<^ 



ALOG 
ALOG 

Ainn 



1/16 Al^5 
l/jft A^7_ 



C? 0^ 

CP 0^ 

1? 0^ 

CI l5 



4TQ4-57 
4To2-4^ 

4Tofi-o^ 
4TH(j*40 

4T^0-04 



^Ko7--fl3 
^''C^-47 



1/^6 Ai4a 

1/16 A274 

-^J^ — A27S 



In i5 



41rto-27 

4T^0'*^ 
41flQ-A7 

4TbQ-7i 

4TH2-49 
4Tt5g-o^ 



4Tb2-27 
4TB2-44 



15 i5 
15 33 
Ifl 3 3 



4Ttt2-7j 
41*16-44 
4Tftft'47 



5Mo7-49 

5Po7-45 

_t;H^7_^4f^- 

^Pr7-5c 

^♦'l^'Ol 



5^15-04 

5^15-06 
5^^5*0'' 



5fi5*ii 

^f- 1^-13" 
5ri5-i5 



CM^5 SVO ALOG 1/^6 A276 ci 34 4Tfl6*7i bP^^^i? 



2 S 



o 

_g_>_ 






o 

I 

CO 

-1 



o 

J 

00 



D='47J2229q2AY rev B FRTS RLprTRICAL SYSteHS SCmEmAT iC/TElEMETR Y MaTrU ^tf^^/lA 



PAGb 






TLM FUNCTION 



l^l|6 :HN ^h SCANNER VInEO nUTpllT 

i5ii7 :hn j7 s^A^l^JEc> vrnpo putpht 

t*>il9 :hn i9 SCANNtP VlTiEO pUtpt^T 

l^iPO :hn ?n SCINNEp VinFO OUTPUT 

I'^ini :hm g ^ sc^NhEp vingn pi i tpht 



i^i?2 :hn 2? Scanner vmen output 
l5i?3 :hn 33 Scanner vineo pUTpuT 



l5i?6 :HANNFL p6 SCANNER VipEO CUTPUT 
16qq^ ^ECErvE*^ 1 Sin STReWQTH 



l6on3 ^ECt-lVER i PWP Supply vniTAGE 
16^,34 ^ECeivEH ? SIPNAL STrFNGTM 
l^OffS i^FCFTWFU g* T&MPEWftTilnF 



|tyf,6 RECEIVER 7 PWP SUPPUy VOLTAGE 



ACROWYK SIGNL SAmP GATE COLUMN VIP S/S I^T 
TYPE SEC ADOR /PpW CONN CCK^ CCnk' 



CH^b sy/0 
CH-i 7 SVO 



ALpG 
ALhG 

CH59 svo alog 

CHpo svo ALOG 
TH^l SV O flLDG 



CH;>2 SVO ALnG 

CH?3 SVO ALOG 

_CKpA_SAtX) AU5G^ 



1/^6 A277 
1/^6 A27e 

iV^i^ A279- 

1/16 A5?7 
t/16 ^536 
-4-H^i Ai^S- 



C? 3^ 4TH6-b: 



1/16 a53o 

X/X^ A53i 

-4yi^ — Aa45- 



le 69 4TV4-49 

Ci 7o 4194-0^ 
CP ^Q 4T94- g 7 



qP 7g 4T94-44 
ao ^0 ^T94-47 

-4^^a^_4a^4^t. 



5Hi5-?3 



CH;,6 SVO ANALOG 1/^6 A393 l5 5o 4T9o*26 ^Hi5*-3o 



RCvRi SG 
RCWR ^ T 



PCVH 1 V 
RCvR^ S6 
ftCvR g -T- 



ALOG 
ALOG 



ALOG 
ALOG 
flLfifi 






Al49 

A go9 



RCVR 



l/l6 AJ36 
U\^ A399 
l/x 6 A.4A4 



4Tfe2-5i 
4 T 8^ -g7 



IP l5 

IP 42 4T'^e*o^ 
1? 51 4T9(j-49 
IP ^ 4 T9£'^ >1 



3Drt-l-2 

3Dq4-3 
?Dn4-2 



2 V ALOG i/3L6 A584 cj 78 4T96-1? ?Do4-3 



P o 

IF 



^63 



2? 



* **'0 1000*?000'6ooHi7QOo*BDOO*11000 * 



I 

CO 

to 






n?47Jgg39ogAY HgV P F^TS ELFCTR|(iAL SYSTEMS SCHewAT Ir/TEl.EMETRY MaTrIX ^t/^9/7A 



FJNC 

NO. 



TLM FUNCTrO^ 



ACflONYH SIf;NL SamP GATE COLUMN VIP Sy£ 

TYPE SEC ADdR /PrfW CONN CC^^ 



IM 
CCnm 



PAGt 



26 



INTfcRFACF SklTCHlWG MODULF CiSM) 



(PART OF ACS S/S» 



10l7 3CANNFR 9 Fm/DTS 



l?5i 3AD LFfT POV'FP UNFUScn/F!i<;ECr 
l29o srNGLP Scanned HOhe m^LHck/LOCK 

lP9l S i r A Mgt^R T>|^<iB<e S c lFhT g / | 

1?^? ^IGHT Cn<;TNE POT nuT 
t?9,^ ,EFT COSINE pnT QijT 



<PAHT OF OA S/3) 
-^f^T^ Q A T H P II STFR HFATEOS n >' /orr 



( PART OF ATT. SENS. S/S ) 



3fi0^ ATTITUDE SEtiSOR OM/Off 
fPART OF THFBMAL Q/R^ 



712? :OMP. LOAD 7 ON/nFF 
JU-^^ :nMP, LOnn P HM /nF-F 



7l3i, AU)f. i.OAn PANf'EL 1, TFHP, 

7a3i Aux. lOAn PANMEL :>, tf*ip. 



< PART OF C. AND' n.H. 8/$ ) 
-^ ^ SFP SUITCM 1 PYRASS mQ/y^S 



9d^1 3FP SwlTrn ? nypAq<; MO/yps 
306? CLOCK FUsPD Pw^^. prI/PED 
■S ll 3 HSFN STAnftN rMAK!^.gt ^^9 O/A 



tJtJpQ JSQ XHTR PRIMAI^Y POWPR OFF/ON 
llO?l JS9 XMTR RECU^^DAnt Pni^ER OFF/ON 
IgpOO itnF R fl Mn _Pflh FP AMP| tFip t^i; 



PHrn/lRV POMFP OFF/ON 
l^inO WIDEBAND POWEP AmPLIFTERS 
REntr^fTANT PnuFP nrF/OM 



(PART OF A.P,U.) 



SCAN 1 DIG d 
SC^N 2 Din B 

-Sixo-pLWj: Dia-a- 



SGI, SCKR DIG B 
SHftN BI S niG B 



COS SlGR 
COS SIGL 



ALDG 
ALOG 



1/16 5B52 
1/16 5R5i 

1/16 5R54 

1/16 5B4e 
-t^t* — &a^ 




1/1* 
1/16 



A3i2 
A3i3 



0? 



02 
01 



<Tn2-l^ 
< To4-i'n 






?*rft 



-Mr 

39 4Te6 



-^^n^ -^-'— '^/^i.v ^i-i^- 

4^0''?5 ^717-11 
4yft5-l4 57i7.p7 



4^0^ * ^ 



•0? 



4Xn5 

4)fo3 



■J6 

-16 



S7l7 



r4- 
16 



5717-13 



THUS M TR nu a — t^^A — ^^a^i^ — ^^_^ — ^ T^^^rAh /ivpj.p? 57^ ?^ 



ATT SENS DIG B 1/16 5B53 c? o2 4Td6-4^ AYf^l^t 57i7-n3 



CMP LD 7 

CMP LP B 




^^0'-4 57l7-n2 

^*^ 57i-7*^vl- 

4X03-48 5737-^5 
4XqE-4B «57i7-i7 



?^ S IPYPS D4.G-„a U^ ^^h IP Qg 4T pg-^:^ 



SS 2BYPS DIG R i/ib' 5RS7 'i5 o^ .4lo2-46 
CtK FUSE DIG B 1/16 5B58 iP f)2 4lfj4-5;i 
-M-5 — XHiJ HTG R 1/^6 AH^fl ^p qo aTp>],«^f^ 



P MSR PU OIG B 1/16 7643 15 oO <To4*29 
f* nSB PW DIG e 1/16 i842 i;> qq 4Tn4-37 



-4 it-e^ •,^5-57i2--p a- 

4xn5-?t 57i7-n^ 

4yoi-?3 57l7-io 
fl VFi?>39 q 7^JL>^x5- 



4^03-12 *i7i7-;>2 



P WPA PW DIG B i/i« 7B42 ig OD ^To4-i3 

B WP l PM nifi R 1/16 <^a44 ^P QQ 4ToA-7^ 



4)eo3*l4 57i7-^3 
4^0 - '''10 ^7i7»p^ 



13210 APU USB/PA P.U.T.StGNAt ENA/DIS \}^p tSIG DIG B i/^b 7B44 



Ifi 00 '^U^-is 



4)*03-o4 57i7-i6 












nP47J2229n2AY WeV B pRTS ELpCTRlCAL SYSTEMS SCMEMAT Ic/TELEmE)RY H4TPIX ^(:/^9/7A 



FJhC 

NO* 



TLM F'JWCTIOW 



ACROwYM SICNL SahP GATE COlUHN VIP S/S 

TYPE Sec aDdr ,/pow conn cc^^ 



CCnK' 



PAGt 



?^ 



<PAHT or PAYLOAD S/Sj 



i4tia :amfr4 no, i 

l42i8 :AHFrA no. 2 



l^Q^S 1SS HFATpR 



OM/OFF 



PN/orF 
ON/OFF 

nN/nrF 



ON/OFF 



aOWFR SWITCHUS MODUlF (PfSHl 



CAmErA 1 
CAMtRA 2 
fAMFBfl 3, 



DIG B 
Dlf5 B 

nin R 



msr syst 

MSS htr 



DIG f3 
DIG 8 



1/16 
1/16 



1/16 
1/16 



6B55 
2B61 
1SR/S3 
8^41 
5B60 



In 02 

1? 3 



In 00 
c? o3 



4To8-2ft 
4Tu6-2i> 



^To2-n4 
4T06-S3 



4X11-42 5717-32 
4Vii»45 57l7-:^y 



4y2;;-4i 57i7-:t7 
4yn3-? 57i7-p4 



(PART OF OA S/S> 



O 
J 



~^-^fl 3A sot Pp y £fl EWA/OU 



203'' 3* TIMER ENA/Dls 
fJAHT nr onupp q/^i 



6o79 3AYL0AD FUSE BLOW Bt}^ Vol TAGE 
6 1 1 P^K ^ i^_RE^-Ay^ n^F | G <| R A TTOM HUE O /Cr 
6I0? P3^ RFl AY nOS FNA/niS 

taART nr a.P-ui 

l32n^ APU fi PAytOAD 9*U,T. sIG EnA/D|S 

-4^3^1 5EAPCK-TBACK_i-j_*3J.JATA^-rn-JlPiJ 

tA*B) NnnM/St'ITCMED 



C^ART OF PAYLQftP S/SI 



1^000 ^SS POWFr FN^'SLE/DIsaBLE 

l4 ii t7 — BBV *;huttfp PtfH nft'/OFr 



-sm^ 



ajJ^^ l^i &a42 1^4 4J o 6 'g fi &a^3^^,e-_^ie,^3 



OA TIHFR DIG B 1/^6 5863 ij (j3 4To8*46 5Fi3-26 57i 



•Pi 



FS BlO V ALOG 1/^6 A337 15 42 .4Tfle-27 5Fi3-io 57l5-il 

S — eH<M — A-G E D | fl .. B ^V-4 •A — f>Bf> A — i-^ &.! 4 T 04*5 ? Sf ^ 3- "^ ?— *i 7 v5— -4^ 

PSM RLYS DIG R 1/16 ii^58 IP o2 ^Tn4'2i 4>o3-?i 57i7-p6 



PL TSIG OJG 8 1/16 7346 c? Dl 4Toe-i3 



ST DATA DIG B 1/^6 7845 ci <Jl ^^ O^^Z' 



5Fl3-o^ 571^-n*^ 
5Fi2-n8 57l5-fi6" 



hSs pwr 

SHtH PkR 



DIG 
DIfi 



l'»4na ^«V M^GNFTIC rOHPPNSATOR ENA/OfS HAn COf^P DIG 8 

I44nl ^HV MAGNETIC rOHP CUppEnt HIGH/LOH HG CmP I DIG 8 

, 44ipi ^RV ^ THFBMOF i FrtPir kOH F^A/nt«; thm ^n ^ nr^ a 



1/16 



7B47 

-SR4<> 



l42?j ^ev p THEPHnE» ECTRTC kOD ENA/DIS THm hD g DIG B 
l43?l ^BV 3 THERHOEl ECTRtC MOD ENA/OIS THh MD 3 DIG B 



1/16 
1/16 



1/16 
1/16 



5B38 
8B40 
7R41 



C8 



01 



4Toe-29 
4To3-4ft 



7B38 
7B39 



CI 00- 
I f . 00 



4Tft8-74 

4T02-27 
^to2-B^ 



5Fi;i-47 57i5-^o 



01 

0? 



00 

00 



4ToB 

-*Toa 



•77 



5Fi5«.^2 57i5-:^2 

5Pl^-?4 57i6,a7 

^F43'35 S7i£ -n ^ 

'n2 



5Pi3- 

5Pi:*- 



46 
38 



6715. 
«>7i5.p3 



»ART OF C AND DH S/S 

iipga JSfl YPTfts nFF .sig PNA/nu 

l3o35 ^TR I CONTROL nOrw/RevERSED 

l3ias tfTR p cn ti TRnt >gnR M /H c vFR Rc D 

l4oi6 ^8V PRIMARY CONTROL ENa/D/S 



^ '^f^^OFF nin R iZ^A ZEAfl 1^-^^ flTpa-ii 5Pi<S'4fl ?'^i'^-p4 



VTP 1 CON tlG B 

vTp p row nin r 



1/16 



1838 

4fi46L 



CI 00 

-«^-oi- 



^Ti,e-6o 
4Toft^37 



&Pl3*3l 
^Pl1- 4 i 



SPLICF 

i; pLirr 



RBV PCON DIG 8 i/i6 1894 c8 02 4To8-2n 5Pi3-4^ RPLlCP 



TT 



n°47J22;9ogAY RFV B fiJlS Et-FCTPfCAL SrSTEMS SCMtHAT IC/TElEMETRY MaTrIX n«/l9''74 PAGt 



i fJNC TLM FUNCTION ACRONYM Sir.NL SanP GATE COLUMN VIP ./£ ,kt 

^ TYPE sec ADDR /POW CONN CC^^ CCnn 



*UX PPOCESSiNf; UNIT APu 



l>J2nl -1.2'' 'iUPPLY Aplt -,nv ALOG 1/46 4465 n. t,4 4T<>o-o7 -.c * = 

l32o7 J4 HiN. PL B.„.T. sTtPT SIG. ON/OFF 34h PL DIG B {At nil ," !. VlH.t t^'t'^l g"^ 

I32n8 54 ftlNUTE USB/PA «.U.T. SfTAHT SIGNAL ^ ^"°^ *To2 8o i^gt-^* ^^ 

—- ■■ — — nn/ O Fg L J4hi_yj;^A OiC-B 4^L^6__ja4a *n - 1 ^ Tm-?. -. ct-,-. 12 £ 

I3at2 PO.EP Mon. .0RH/ST5Y p.. HODE DU B t7!6^tt? nt"tlt|:ir-t "^t:?! R^ 



i/l6 1848 a(j 01 ^To2-2o 3^0^-1^ O ^ 






i7 !„ i . F r . n. Tn . rK , . V ^,, %l\\\l l\% \ M} l\-} '^-^ \VV^lX"^ ^^^1! 



1©- 



THF FO ll flHlNB AflC uTit tTcn ar c pgrHL FiiwrTtnMg fe q 



^K 



30 



nP47J2229Qi>AY RlrV H fHTS EUfcTPICAL SYSTEMS SCHeMA Uc/TPI EM6TRY M^TrU Qt/^9/74 



rJNC 
MO. 



TLM FUncTIOW 



PAGt 



31 



ACRONYM SIGML SamP GATE COL^J^N VJP ?yS IM 
TYPE sec AD.DR /fow conn cc^^ CCnm 



( PART OF POWpf? S/S \ 



,^fl^^) — SHU^T- LOA H ^CJiiiRF-MX- 



6oBi 



3HUM LOAn 7 rURRPNT 
SHUNT lOAH 3 PORRPnT 

SHU^lT Lf.Mn <i riJWRPfviT 



^084 5HUNT LOAD 5 riJRRFNT 

S0B5 5HUM LOAn 6 rURRPNT 

-6^ flA _41-iUfci t: -4J1AJ1 7 nURfl ^. Wt 

6n97 SHUNT LnAn a rURRFNT 

6o89 SHUNT LOAP ^A^ OM/OpF 

-^^^^5 — 5H J JLT L O A n *9^ — QM/nrr 



609t 



SHu^T loah ^Crf on/Off 

SHUNT LOAH ^D^ OM/OFf 

AilXlLPAf^y LOAn ? ON/nFF 

^U)ClLURy LOAr ,i nN/OFF 

ftlUTlJARY LOAn 4 SK^iilEX, 



6o97 ^UXlLFA^Y LOAn 5 QN/nFF 
IPART nF_THFflMAt ft/ S| 






:oHP LOAn 1 
roMp iriAD g 



nN/OFF 
ri;^/OFF 



7l23 ^OMP tOAO 3 pN/OFF 
7l2^ -OMP I QAn A r'J/OFF 

-JLj aS — ;o H&_ UO AD -5 diUarfl- 

712^ :OHP LOAn 6 rN/OFF 

L^ART OF rtPH S^SI 



9057 riCK/TOCK TjC/TnC 



_£KiliLr.j_4 AUaO- 



SHIINT2 I 

SHUNT3 I 
SHUNT 4 I 



AUnG 
ALnG 
ALori 



SHUM5 I 
SHMNT6 I 



SHtlNT6 I 
SHHNT A 
SHtiNT P 



ALnG 

alog 

DIG B 



SHMNT C 

SHiiNT D 



DIG B 

DIG B 

411-G^-B^ 



AUy lD 2 
AUy LD 3 
faijy LP A 



DIG Ej 
DIG B 
DIG P 



AUv LD 5 DIG B 



/l6 

yi6 

/l6 



^ 1 (iZ~ 
A167 
A23l 



In 1® M^j-34 

12 2^ 4rfl4*34 



/16 



4-^ 

/l6 

/l6 



A359 

A>123 

^A4A.7™- 

A55i 

0^59 

fy046 
0^53 



lP^?-0^ 
1^ ;$ 6 4 Tri 6 -3 rt iPi^^-iP 



18 45 

Cl 55 

Ct 00 

Cl 01 



4TH8-34 

4T9(j-3'» 

^JJ.2_-3il 

'1T'>4-34 

4X06*84 



-.3F45- 0^ 
5P^?'2l 
lF^J-39 



Cl n2 

Oj 03 

C? Dl 

0? 02 



o6-4n aF^p-or 



4To6-4.^ 
4Tn4-62 

47tj8-6^ 
4To6-3f^ 



''1^ o^<^2 lo o3 .4Tne*2:5 



iP4s-ni 
3P45-4? 

1F45-36 
lP42'3P 



CMP LD 1 
PHP LP g 



DIG e 

DIG B 



CMP LD 3 

CHP LD 4 
GMP LP ^ 



DIG 8 

DIG B 
DIG S 



1/16 



765o 



1/16 7653 
t/16 7854 

™Ut6 7H55 



15 01 
01 pg 



C? 2 
OP 02 



4To4»6n 
4Tn6'ft(j. 



^Tn6-7l 

-*To8-eri 



lP42-o9 



lF4?-2ft 
-4J^^5^--23^ 



CHP LD 6 DIG B 1/46 7B56 12 o2 *To2-76 1P42-24 



TIG/TOC DIG B 1/1 9B36 17 03 



I 

CO 



APPENDIX D 
STRIP CHART PAYLOAD SIGNATURES 



APPENDIX D 
STRIP CHART PAYLOAD SIGNATURES 

Figure D-l is a strip chart (General Status 2) showing characteristic signatures of payload 
equipment. This record is made from a Narrowband tape recorder playback showing 22 
frames of Wide Band Video tape recording, RBV, MSS, WBVTR-1 and WBVTR-2 were 
operating during this time period. The Wide Band Down Links were off. Increasing time 
is from right to left. The 17 pens are alternately analog and digital. The parameter values 
drawn by each pen are described below. 

Pen #1 shows Greenwich Mean Time at the time of recording, as measured by the recording 
ground station. For example, the last time code, (left hand side) reads (binary): 

01 0010 010 1001 000 0000 which converts to 12:29 digital. 

Pen #2 shows spacecraft regulated bus current. The MSS is supplied from this bus. The 
first step- up (reading right to left) is the time of MSS turn^on. It reads 1.2 8 TMV (4. 57 
amps) before turn-on and 1. 76 TMV (6. 19 amps) after turn-on, the delta 1. 62 amps being the 
MSS current demand. 

Pen ^3 shows two digital functions, the short duration function being MSS System ON, and the 
long duration function being Hi Voltage ON. (The elevated region is ON. ) The non-coincidence 
in time between this Pen and Pen #2 Is due to the sequential sampling format. 

Pen #4 again shows duplexed functions, both relating to the Wide Band Power Amplifier No. 1. 
The bottom horizontal lines (reading zero, showing the WBPA was OFF) show the voltage of 
the +15 V A supply; and the top horizontal lines (reading 2. TMV equal to 17. O^C) show the 
temperature of the collector. 



D-1 



Pen #5 shows the duplexed functions of RBV 24 Volts ON and RBV Shutter Power ON, 

Pen #6 is similar to Pen #4 except it shows the parameters for WBPA No, 2 which is 
normally associated with the MSS. 

Pen #7 shows duplexed function for RBV Magnetic Compensator ON and CCC Power ON, 

Pen #8 shows the duplexed functions of Wideband Video Tape Recorder footage s, the 
top horizontal lines associated with WBVTR-1 and the bottom lines with WBVTR--2. At 
the beginning of the RECORD session, the footage read 2.23 TMV (equal to 10. 03 Min) for 
WBVTR-1 and 2.77 TMV (equal to 16,63 Min) for WBVTR-2. At the end, the correspond- 
ing footages are 20,43 min for WBVTR^l. and 25. 79 min, for WBVTR-2, 

Pen #9 shows whether WBVTR-1 is in Rewind, It reads zero (depressed) showing that 
WBVTR-1 is not in the Rewind mode. 

Pen #10 shows WBVTR-1 input current. At Record Command, the current rose to 3, 95 
TMV (equal to 3, 59 amps) after a brief saturation transient in excess of 8, 18 amps. This 
transient is a characteristic signature of WBVTR turn-ON. 

Pen #11 is duplexed to show Record and Playback modes. Because of the fast run time of 
the strip recorder, the brief interval between sampling and the mode displayed, the line 
blurred, making reading impossible. 

Pen #12 duplexes the reflected power in the antenna systems of WBPA 1 and 2, Because 
both these systems were OFF, the readings are zero. 

Pen #13 shows whether WBVTR-2 was in Standby or Rewind mode. It can be seen the 
top horizontal segment went ix) zero at start of record, terminating the Standby mode. 



D-2 



Pen #14 shows the Payload Regulated bus current, with its easily recognizable characteris- 
tic signature of RBV and WBVTR activity. After turn-on and warm-up, the WBVTR's can 
be seen suddenly increasing the current drain and producing characteristic WBVTR turn-on 
transient, WBVTR-2 first followed immediately by WBVTR-1. 22 RBV camera exposures 
and readouts can be seen. During this interval, it can be seen from Pen #8, that the scenes 
are being recorded on the moving tape. Turn- OFF is seen to be simultaneous for RBV, 
MSS and both video tape recorders. 

Pen #15 shows whether WBVTR-2 is in Record or Playback mode. Again the fast speed of 
the strip chart and the proximity of sampling times obscures the message* 

Pen #16 is identical to Pen #10 showing Recorder Input Current except that it relates to 
WBVTR-2. It can be seen that Recorder 2 comes on before Recorder 1, 

Pen #17 shows GMT as measured in the Spacecraft at the time of data sampling. 



D-3 



OfilGINAL PAGE IS 
OP POOR QUAUTY 




\ S/C GMT 



WBR-2 In. Cur 
WBR-2 Rec/P.B, 



!.J_; P/L Reg Bus Cur 
^ WBR-2 STBY/R.W. 



MPA Refl Pwr 1/2 
WBR-1 Rec/P.B. 



(8) jiummmj^iimiia.jujjj^^^j^j^j^^ 



WBR-l In. Cur, 
WBR-1 R/W 



Footage WBR-1 
Footage MBR-2 



®- 



f ^ 



- RBV Mag. Comp ON 
CCC Pwr ON 



® iiiiiiiiiiiiiiiiiii 

(5) 



® 

(D 
® 



lilill 



iill 



WBA Col .Temp #2 

WBPA +15V Sup #1 
RBV 24V ON 



, L Shut. Powr ON 



■■■■■■■MIWlMaiB 



... 1^^ — .i.^ .. ■ . .. 1 ^ .^1 C 



ti..m i*i^^..lk.t.L. ^t^i^.^. ^. . J L I ■ . ...J, , t^,. , .j^.. .. , 1- J 






I mt M * m m nu n ^ i^i ■■ i k ^ ,jtt^t ^t mi^tmts 



WPA Col Temp #1 

WBPA +15V Sup #1 
HSS Sys ON 
Hi Volt ON 



S/C Reg Bus Cur 
Gnd Sta. GMT 



Figure D-1. Characteristic Strip Chart Payload Signatures 



D-4 



APPENDIX E 
MSS PHOTOGRAPHS 



APPENDIX E 
MSS PHOTOGRAPHS 



Hepreseutative imagery from the MSS is shown in the following figures. Spectral bands are 
given in Table E-1. 



Table E-1. MSS Imagery 



Figure 


Band 


Wavelength 

(Microns) 


System 


E-1 


1 


(0.5-0.6) 


MSS 


E-2 


2 


(0.6 - 0.7) 


MSS 


E-3 


3 


(0. 7-0.8) 


MSS 


E-4 


4 


(0. 8 - 1, 1) 


MSS 


E-5 


4, 5 and 7 


(*B&W Composite) 


MSS 



*B&W Composites of MSS use three bands - 4, 5 and 7; or 4, 6 and 7, 
Note: Bpud Imagery is annotated MSS 4, 5, 6, 7, and 457 (composite)* 



All photographs sow the same ground scene, 185 x 185 square kilometers in area. The 
scene covers a segment of the California coast from Monterey (bottom center) to Napa (top 
edge near left). The Golden Gate just above San Francisco is at upper left. Stockton is located 
just under circular break in clouds (right of center, just below top). Clouds cover the San 
Joaquin Valley. Sacramento is 30 miles to north of picture center. Pacific Ocean is at lower 
left. San Pablo Bay and San Francisco Bay are clearly visible near San Francisco, and at 
lower ri^t San Luis Reservoir is seen. Water pollution is seen in San Francisco Bay, intense 
near Oakland International Airport and stretching across the Bay to near San Francisco 
International Airport. 



E-^l 



"■^S^oS? 




2JJR^i'^3s, 



^P h M3^-2^^U}7l -"^"^ ^St ^- " bJl\ 






y 1 22-30^ 



ijjaa m 




mi -321 



Figure E^l, 



E-2 



r' • i.i ' 



l.\7' 'Wi 




L. j 



i 



\ i 



w;22-M 



Figure E-2a 



E-3 



-^«^.^^« 



^\?2 m-: 



w:2!-^- 



'2-^ 




^\22-W 



Figure E-3. 



E-4 



T^^^ PAGE IS 
OF POOR QUALITY 



^i??"gP<! 





i 1 




^,i22-'iig ■..-2Z-m^ »\2-3^: 1^0^b-3i^ 



Figure E-4. 



E-5 



OBIGINAL PAGE IS 
0^ POOR QUALITY 



^,22 -m^ 



.^^ 




I 









^t^g^ le^?-^^ '^- 



ui2^-:^J 



I«i22-Bei 



;^^,^ir^i 



Figure E-5. 



E-6 



APPENDIX F 
PIR U-1N23-ERTS-130 
DCS OPERATIONS EST LANDSAT 2 



GENERAL^ ELECTRIC 

SPACE DtVISrOht 
PHIlADCL^HtA 

PROGRAM INFORMATION REQUEST /RELEASE 



•CLASS, LTR, [operation PROGRAM |S£QUCNC£ NO. llftCV. LTR. 



PIR NO. 



I OPERATION I PROGRAM f 

1N23 ^ ERTS 



130 



•use *'C" for classified ANO "U" FOR UNCLASSlFfCO 



FROM 



K.S. Rlzk 



Tg 



T*W, Winchester 



DATE SENT 

12 February 1975 



DATE INFO* RCQUtRED 



SUBJECT 

DCS Operations in UNDSAT-2 



PROJECT AND RCQ. NO, 



REFERENCE OIR. NO. 



INFORMATION REQUESTED/RELEASED 
INTRODUCTION 

The Data Collection Subsystem (DCS) was turned off in LANDSAT-1 after orbit 12690 
on January 19, 1975, and has remained off ever since. In LANr)SAT-2 the DCS was turned *:' 
on in orbit 5 on January 22, 1975, and has remained on since. This study is to compare C 
the effectiveness of the system before and after the changeover. 

SUMMARY 

The effectiveness of the Data Collection System is at least as good with LAKDSAT-2 
as with LANDSAT-1. 

DISCUSSION 

Using a data span from a month before the launch of LANDSAT-2 to the present, it 
is possible to plot the continuity and trend of DCS messages received in OCG. With 
this data it is possible to compare the effectiveness of the DCS in IANDSAT-1 with that 
in LANDSAT-2, 

Figure 1 shows the number of DCS messages received daily at OCC, and the number 
of active platforms each day. 

Despite a substantial decrease in the number of active platforms since LANDSAT-2 
assumed DCS operations, the total number of messages received has remained substantially 
the same. The sinusoidal effect of orbital drift on the earth's surface during the 
18-day cycle is apparent in Figure 1 for both LANDSAT-1 and LANDSAT-2. 

In order to provide a more equitable comparison, a plot was made in Figure 2 of 
the messages per day per platform. From this it can be seen that the Data Collection 
System using LANDSAT-2 is at least as effective as that using LANDSAT-1. 

The data in Figures 1 and 2 permit an examination of 1-station versus 2-station 
operation* In the first 3 days, the Greenbelt DCS ground station equipment was inoperative 
leaving only the Goldstone station to receive messages. In that period about 610 messages 
were received daily, about 6.5 messages per day per platform. At a time 18 days later, 
when the orbital ground traces on the earth were the same, both stations were operating. 
The daily message count was then about 930, about 9 messages per day per pUtform. 

From Figure 2, the average number of messages received per day per platform is about 
10 for LANDSAT-1 and about 11 for LANDSAT-2. 



f\ * Z ' fZ^k 



. K.S. Rizk. Svstfems Engineer 
Dist.: B. Phucas 
H. Boys 
Oper Supr» 
R. Devlin 
E, Painter 



L. Gonzales 

L* Smith 

J. Seitner 

K. Riak (4) 

J. Williamson 



^ftETENTlON REOU1REMGNT* 



COPIES FOR 



Q. 



□. 






MASTERS rOR 



Q. 



d 



J I ia MOB, 



□_ 

a 



&0«iTDCiTi*3- 



F-1 



I 
to 



LANDSAT-1 



LANDSAT-2 



1200 



1100 



1000 



900 

LiJ 

< 800 

tn 

ill 

> 700 
J 

^ 600 



500 
400 





' MESSAGES* 13 





PLATFORMS 



ENT 



OFF 



I I L 



[off] [off 



J \ \ L 



± 



21 25 29 

DECEMBER 



10 14 18 22 

JANUARY 



J L 



26 30 3 7 11 

FEBRUARY 



120 
110. 

IOC- 
go 

80- 
70 . 



0) 
a: 

s 

I- 
< 

a 

lij 

> 

U 
< 



Figure 1. Data Collection System Performance 



LANDSAT^l 



LANDSAT-2 



13 



12 



11 



10 



6 - 



2 

g 
ii. 

< 

q; 

Lii 

< 

Q 

q: 

Lii 

en 

UJ 

< 

CO 

tn 

UJ 

5 




M 



I* ^( M ^1 



GOLDSTONE 
ONLY 



DCS 
OFF 



I 

CO 



L 



_L 



X 



21 25 29 
DECEMBER 



± 



J_ 



10 14 18 22 

JANUARY 



26 



30 



3 7 11 

FEBRUARY 



Figure 2. DCS Normalized Performance 



APPENDIX G 
SPACECRAFT ORBIT REFERENCE TABLES 



LANDSAT-2 



SPACECRAFT ORBIT REFERENCE TABLES 

FROM JANUARY 1975 THROUGH DECEMBER 1975 
ORBITS THROUGH 16123 
FLIGHT DAY THROUGH 1156 



G-1 



lANIiSAT-2 
JAN /1975 





1 6MI 


1 FLlta^iT 


1 SPACECRAFT 


1 keference 


i"kef" 


i Cycle' 1 


1 Date 

4^ * ^ * ■■ « i^ 


1 DAY 


t Day 


I OHBITS 


1 - eRBITS 


1 Day 


t t^b* ( 


1^ 


[ 


1 J 
1 


1 *" 
1 ■ 

[ ^ 
i * 


1 * 

1 * 

I m 

1 >* 
m 

i» 

1 m 






1 22 


22 1 


1 J 
1 

t J 
i 
1 
1 

■ '■ 1 

1 

' 1 

1 


fi 

m 

0-3 


! ^ 
m 

m 
m 

m 

150- 153 


11 1 


1 


1 23 1 


23 1 


1 1 


4 - 17 1 


154- 167 1 


12 1 


"1 1 


1 24 


24 1 


2 J 


18-31 1 


168- 181 1 


13 1 


— 1 1 


1 25 


25 1 


3 j 


32-45 I 


182- 195 1 


14 1 


_ 1 1 


1 26 1 


26 1 


^ j 


46-59 1 


196- 209 1 


15 1 




1 27 


27 1 


5 1 


60-73 1 


210- 223 1 


16 1 


_ 1 1 


1 28 1 


28 1 


6 1 


74-87 1 


224- 237 1 


17 1 


-1 i 


1 29 j 


29 ) 


7 1 


88-95 1 


238- 245 1 


18 1 


~ 1 1 




29 1 


7 j 


96 - 101 1 


9- 14 1 


1 1 


t 


1 30 1 


30 ( 


8 1 


102.115 1 


15- 28 I 


2 t 


1 


1 31 1 


31 1 

> « V « ^ * fl 


9 1 


116 - 129 1 


29- 42 1 


3 1 


1 



ORIGINAL PAGE IS 
OF POOR QUALHY 



G-2 



LANDSAT-2 





1 'Jfi-I 


1 F 1,1^^7 


1 SPALL"'. 


■ h.^fj 


1 Kt:F£RE..CE 


rlF" 


1 CYCLt- 1 


i i^ATL 


i Qm-Y' 


DrtY 


r 'JKbiTb 


aRBITS 


DAY 


1 NU. ! 


1 1 


1 32 


10 


1 130 - 


131 


1 43-44 


4 


1 1 




1 32 


1 10 


1 132 - 


143 


1 59-70 


5 


1 1 


1 2 


33 


11 


1 144 - 


157 


1 71-84 


6 


1 1 


1 3 


1 34 


12 


158 - 


167 


1 85 - 94 


7 


1 1 




34 


12 


1 168 - 


171 


109 -112 


8 


1 1 


1 '^ 


! 3b 


13 


i l/c- 


i«5 


! 113-126 


9 


1 1 


1 'j " 


1 36 


■ 1^ 


liJo- 


l9a 


127-139 


10. 


\ ' 1 


1 ^ 


J 37 


lb 


ly^j- 


:>1^ 


Ho-lb3 


u 


1 1 


1 ^ 


1 3a 


■16 


1 213- 


226 


15J*-167 


12 


1 1 


1 ^ 


1 sy 


■ 1/ 


1 2'd/' 


2^+0 


ib*i-l?^l 


13 


1 1 


1 ^ 


1 4 


la 


1 ^'ti- 


2b^ 


182-195 


14 


1 1 


1 10 


1 . tl 


1 ly 


' -cbb- 


ZbS 


1 lS6-20y 


15 


1 1 


1. il 


•+C 


zo 


1 . £fay- 


262 


210-223 


16 


1 


1 12 


I 'ta 


ai 


?f83- 


296 


224-257 


17 


1 


1 i'^ 


4^ 


2£ ■ ■ 


237- 


310 


23a-25l 


16 


Q ! 


( 1'+ 


1 tb ■ 


dd 


,3;li- 


324 


1- 14 


1 




1 IS 


[ ■ ^6 ■ 


■ ■:■ 2f ■ 


( ■ 325- 


335 


15- 2S 


2 




( 1" 


1 V7 


^b 


33^* 


.362 


29- 42 , 


3 




1 17 


■ 46 ■ 


L't- 


3b 3-. 


366 


43- 56 


4 




1 lii 


^y 


t;7 


36/- 


38U 


57- 70 


b 




1 ly 


bo 


se 


3S1- 


354 


71- 54 


6 




r 20 


&i 


c;y 


3yo- 


H06 


85- 'Ji- 


7 




1 ci 


b'd 


30 


- iiQ9-- 


^22 


■ 99-liS 


8 




1 ?.t 


b'd 


31 


^23-' 


t3b 


■ 113-126 


9 


1 * I 


i 23 - 


b^ 


32 


43 7- 


f49 


127-139 


10 




1 'a^ 


bb 


33 


^bij- 


^63 


14o-.ib3 


U 




i ab- 1 


56 


■ ■ ■ ■ s'f ■■ 


Mb'^' 


477 


154-167 1 


12 




1 i^t, j 


b7 


■3b 


Wd" 


491 


16i<-lJ<l 1 


13 ■ 




1 27 


bis 


... .......^(j..-. 


r- 'tyr:-' 


505 


ia2-r-^5 1 


• 14 




1 26 


by 


3/ 


50o- 


519 


196-209 


15 





OEIGINAL PAGE. IS 
OF POOR QUALITY 



G-3 



"LAKiOSAT-? 
■"HAl^i. 1 97?; 



1 1 

r--T)-ATF"~r 


GMT 
"DAY- 


1 Fi'lbHT 1 RPACfCRaP't"! REf^FSFNCp" 
1 -DAY" r -"-ertSiTfi "1 ■" fiWE\:Ts" 


""re*-""'* 

i DAY |- 




w ■« 


■ 1 V 1 

1 p 1 


-60 
^1 
62' 

^3 
--ft# - 

hB 
-t>6 - 

^7 
ft 8-1 

70 - 
71 

Td 1 

73 
- 7<» -1 

75 1 


1 38 ---| "Sao- ?533- 1 ?1n-??3 

1 39 1 H34- c;47 | ??ii-237 


1 !*=> 1 
1 17 1 

r— 18 -r 
1 1 \ 

\~ ? r 

1 3 t 

1 B 1 

1 -ft 1 

1 7 1 

r" 8~ 1 

1 9 1 
1 m 1- 
1 11 1 
1 IP 1 

1 13 ( 

, -14 -i 

1 15 1 

f- 1ft 1 

17 1 

18 r 
1 1 

1 — -p-f- 

3 1 

5 1 
- 6 |- 
7 i 

R-|- 

9 1 
- 10-1 


1 
1 

2 

2 

2 
2 
2 

2 • 

2 
2 ■- 

2 

2 

2 

2 
2 

2 

? 

2 ■ 

2 
- 2 

3 

---3-- 

3 
3- 

3 

--- 3 

3 

3 

3 ■■ 




1 3~ 1 

1 ft 1 

1 — 7- r 

1 ^ 1 

1 10 1 


1 4 1 ~ ■ B 4 a i - R ft 1 1 3 -^R » P =• 1 - 

1 41 1 56?- R7S t 1- 14 

r -42 --7 — S7ft-— '^Rg-t -■!=;- ;3R 

1 43 1 590- An3 j ?q. 4? 
r " 44 i — 604- -Al 7 1 4q- ?»6 " 

45 1 61ft- A31 1 57- 70 
^6 \~ ft3P- -A4R- 1 - - 71 - S4 

47 1 64ft- ftB9 1 «R- <38 


r 


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1 1? 1 

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1 ..^ g. — ^ -66-n-- — fi7 3 - 1 <5q - 1 1 ? - - 

49 1 674- ^R7 1 liq-1P6 

fiO- 1 - 6S8- 700 1 lP7-13g 

51 1 701- 714 1 14n»1F^3 

r- -52-- -1 • 715- - 7PR 1 1S4-167 

b3 1 729- 740 1 JAR-1«1 




1 17 1 
1 Ifc 1 


76 1 

77 i 
-78 1 

79 1 


r " "&4~ 1 743-- -7ti;ft -[ IRpifqc; — 

b5 1 7S7- 770 1 1*9^. P09 




1 1 y 1 

1 PO 1 


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1 pp 1 


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58- -| 79«3----Rl? r -23R-PK1 
b9 ( 813- HP6 1 1- 14 




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